JPH0589849U - Gas turbine engine - Google Patents

Abstract

(57) [Summary] [Purpose] The amount of dilution air supplied to the transient duct of a gas turbine engine is kept constant regardless of temperature changes. [Structure] The outlet end of the burner liner 83 of the combustor 12 and the inlet end of the transient duct 23 are connected to each other in a non-contact state via a gap formed by the stepped portion 83 ₄ of the burner liner 83, and the transient Duct 23
The dilution air is introduced into the space through the air introduction hole 83 ₃ of the burner liner 83 and the gap. The stepped portion 23 ₄ periphery and transient duct periphery distance is kept substantially constant regardless of temperature changes, the amount of dilution air introduced from the gap is also kept constant.

Description

[Detailed description of the device]

[0001]

[Industrial applications]

 The present invention relates to a gas turbine engine in which a burner liner, a transient duct, and a scroll are sequentially connected and arranged inside a casing.

[0002]

[Prior Art]

 Conventionally, dilution air is introduced from the clearance formed between the burner liner and the transient duct in order to lower the temperature of the combustion gas generated inside the burner liner of the gas turbine engine and prevent burnout of the turbine. Are known (see Japanese Utility Model Publication No. 61-9264).

[0003]

[Problems to be solved by the device]

 However, in the above-mentioned conventional gas turbine engine, the clearance is formed by making the outlet end of the burner liner and the inlet end of the transient duct face each other. If the thermal expansion occurs, the size of the clearance increases or decreases and the amount of dilution air introduced becomes unstable.

The present invention has been made in view of the above circumstances, and an object thereof is to always introduce a fixed amount of dilution air into the transient duct regardless of temperature change.

[0005]

[Means for Solving the Problems]

 In order to achieve the above-mentioned object, the present invention is a gas turbine engine in which a burner liner, a transient duct, and a scroll are sequentially connected inside a casing, and the burner liner and the transient duct are independently capped. The first feature is that the outlet end of the burner liner and the inlet end of the transient duct are superposed on each other in a non-contact state and connected to each other.

According to the present invention, in addition to the above-mentioned first feature, the transient duct is curved so that a surface formed by its inlet end and a surface formed by its outlet end are orthogonal to each other. This is the second feature.

In addition to the above-mentioned second feature, the present invention allows the outlet end of the transient duct to slidably abut the inlet end of the scroll, and the first support means provided in the casing. The third feature is that the transient duct and the scroll are connected by the pressing force applied to the transient duct.

According to the present invention, in addition to the above-mentioned third feature, the casing is provided with a second supporting means for applying a reaction force of the component of the pressing force that does not contribute to the coupling between the transient duct and the scroll. Is the fourth feature.

According to a fifth aspect of the present invention, in addition to the above-mentioned fourth characteristic, the second supporting means includes a joint means capable of absorbing relative movement and relative angular displacement between the casing and the transient duct. Characterize.

[0010]

【Example】

 An embodiment of the present invention will be described below with reference to the drawings.

1 and 2 show a schematic structure of a gas turbine engine according to a first embodiment of the present invention. The two-shaft gas turbine engine G covers a bottomed cylindrical outer casing 1, an annular heat exchanger housing 2 connected to a rear opening of the outer casing 1, and a rear portion of the heat exchanger housing 2. An exhaust housing 3 is provided. An intake passage 6 having an air cleaner 4 and a silencer 5 is connected to the front part of the outer casing 1, a reduction gear box 7 is arranged at the center of the exhaust housing 3, and a lower part of the exhaust housing 3 is provided. The exhaust duct 8 is connected.

A centrifugal compressor 9 for compressing the air sucked from the intake passage 6 and a centrifugal high-pressure turbine 10 for driving the compressor 9 are provided before and after the central opening formed in the outer casing 1. The low-pressure turbine 11 of the axial flow type for arranging the output is provided behind it and for driving the high-pressure turbine 10 and the low-pressure turbine 11 in the upper space of the outer casing 1. A combustor 12 for generating the combustion gas is disposed. Inside the heat exchanger housing 2, an annular heat exchanger 13 for recovering the thermal energy of the combustion gas that has passed through the turbines 10 and 11 and heating the intake air is provided in the speed reducer box 7. A planetary gear type speed reducer 14 is arranged so as to surround the outer periphery, and inside the speed reducer box 7, the output of the low-pressure turbine 11 is decelerated and taken out to the outside.

A high-pressure turbine shaft 16 is rotatably supported at the center of a compressor casing 15 provided in the outer casing 1, and a compressor rotor 17 having a large number of blades formed on its outer periphery is mounted on the high-pressure turbine shaft 16. Fixed. The air sucked into the compressor casing 15 from the suction passage 6 is compressed by the compressor rotor 17, passes through the radial air passage 19 formed between the outer casing 1 and the inner casing 18, and goes backward. Supplied. The front end of the high-pressure turbine shaft 16 is connected to auxiliary equipment such as a generator and a starter housed in an auxiliary equipment housing (not shown).

At the rear end of the high-pressure turbine shaft 16, a ceramic high-pressure turbine rotor 20 having a large number of blades formed on its outer periphery is fixed. The high-pressure turbine rotor 20 includes a ceramic back plate 21 and a high-pressure turbine shroud 22. It is stored in between. A ceramics scroll 24 connected to the combustor 12 via a ceramics transient duct 23 is disposed outside the high pressure turbine shroud 22, and the inner periphery of the scroll 24 and the outer periphery of the high pressure turbine rotor 20 are disposed. A plurality of nozzle vanes 25 are provided between and. The scroll 24 is supported from the outer periphery by a plurality of support mechanisms 26, and the transient duct 24 is supported by other support mechanisms 27 and 28.

A collector housing 29 is supported at the front end of the heat exchanger housing 2 connected to the rear portion of the outer casing 1, and a low-pressure turbine shaft 30 is supported at the central portion thereof. A low pressure turbine rotor 31 made of ceramics is fixed to the tip of the low pressure turbine shaft 30, and a large number of blades formed on the outer periphery of the low pressure turbine rotor 31 are fitted to the inner surface of the low pressure turbine shroud 32. The low pressure turbine shroud 31 and the high pressure turbine shroud 22 are connected by a low pressure turbine duct 34 having a variable stator vane 33 at the rear end. The low-pressure turbine shaft 30 is connected to the output shaft 35 via the speed reducer 14.

An arc-shaped opening 29 ₁ is formed in the upper half of the collector housing 29, and the collector housing 29 gathers from the air passage 19 to the upper part of the exhaust housing 3 and then passes through the upper half of the heat exchanger 13 for heating. The generated air is supplied to the inside of the inner casing 18 through the opening 29 ₁ . On the other hand, an exhaust gas passage 29 ₂ is formed in the lower half of the collector housing 29 to guide the exhaust gas passing through the low pressure turbine shroud 32 to the lower half of the heat exchanger 13.

A ring gear 36 is mounted on the outer circumference of the heat exchanger 13 over 360 °, and a flat supporting surface formed on the front part of the ring gear 36 has a plurality of guide rollers provided on the inner circumference of the heat exchanger housing 2. It is rotatably supported by 37. A pinion 39 that meshes with the ring gear 36 is fixed to a rotary shaft 38 that supports one guide roller 37, and the heat exchanger 13 is rotated by rotating the rotary shaft 38 with a heat exchanger drive motor 40. To be done.

As is apparent from FIG. 2, the scroll 24 includes a rotation axis of the high-pressure turbine 10 and is divided into four parts by two surfaces that are orthogonal to each other. The first piece 41, the second piece 42, and the third piece. 43 and a fourth piece 44. That is, the two end faces of each of the pieces 41 to 44 are formed as simple planes that form 90 ° with each other, and the pieces 41 to 44 are abutted against each other at the joint surfaces a, b, c, d, and integrally formed. Retained.

Next, a support structure of the scroll 24 using the support mechanism 26 will be described with reference to FIGS. 3 to 5. The eight support mechanisms 26 press the respective two portions of each of the pieces 41 to 44 inward in the radial direction in order to bring the joint surfaces a to d of the four pieces 41 to 44 into close contact with each other. The other structures are all the same except for the length of. That is, the support mechanism 26 includes a support shaft 45 having a pressing member 46 attached to the tip thereof and a columnar portion 45 formed at the base end of the support shaft 45. ₁ A cylindrical support member 47 for slidably supporting the shaft in the axial direction, a spring seat 48 screwed to the outer end of the support member 47, the spring seat 48 and the cylindrical portion 45.₁And a spring 49 which is compressed between the support shaft 45 and the scroll shaft 24 and biases the support shaft 45 inward in the radial direction.

A flat receiving portion 24 is provided on the outer periphery of the piece 41 of the scroll 26, which is given as an example.₁ Is formed, and this receiving portion 24₁The opening 50 of the support plate 50₁The pressure receiving member 51, which is loosely fitted to and prevented from coming off, abuts. A conical pressure receiving surface 51 is provided outside the pressure receiving member 51.₁While the pressure receiving surface 51 is formed on the pressing member 46,₁Hemispherical pressing surface 46 that engages with₁Is formed, whereby the pressing surface 46 is formed.₁And pressure receiving surface 51₁Make line contact along the circumference. As a result, even if the angle changes between the pressing member 46 and the pressure receiving member 49 due to the thermal expansion of each portion, the conical pressure receiving surface 51 is formed.₁And hemispherical pressing surface 46 ₁ As a result, stable line contact can always be obtained, so that the scroll 24 can be supported in a state in which the contact surface pressure is kept low.

The flange 47 ₁ formed on the support member 47 is fixed to the boss 1 ₁ of the outer casing 1 by a bolt 52, and its inner end portion is supported by penetrating the inner casing 18. That is, an annular slider 54 is attached to the guide member 53 provided in the opening 18 ₁ of the inner casing 18 so as to be slightly movable, and a circle formed by two conical surfaces on the inner circumference of the slider 54. The outer periphery of the support member 47 contacts the circumferential edge 54 ₁ . Therefore, the radial displacement due to the thermal expansion of the scroll 24 and the inner casing 1 is absorbed by the expansion and contraction of the spring 49, and the axial displacement or circumferential displacement of the scroll 24, the outer casing 1, and the inner casing 18 is caused by the slider 54. Is absorbed by sliding on the guide member 53 and the support member 47.

Since the four pieces 41 to 44 are supported by the eight independent support mechanisms 26, no matter how much the pieces 41 to 44 are thermally expanded, excessive stress is applied. The scroll 24 can be reliably supported without causing

As is apparent from FIG. 2, the inlet end portion and the outlet end portion of the transient duct 23 are cut along a plane that makes an angle of 90 ° with each other, thereby facilitating manufacturing and improving processing accuracy. The outlet end of the transient duct 23 slidably abuts against the inlet end of the first piece 41 of the scroll 24, and is pressed by the pair of support mechanisms 27 and 28 provided in the outer casing 1 in the opposite directions. Will be retained.

As shown in FIG. 6, the support mechanism 27 of the transient duct 23 includes a support shaft 45 supported by the outer casing 1 via a support member 47, and the transient duct 23 via a pressing member 46 and a pressure receiving member 51. It is configured to press the receiving portion 23 ₁ formed in. Since the structure of the support mechanism 27 is substantially the same as that of the support mechanism 26 of the scroll 24 described above, duplicate description will be omitted by assigning the same reference numerals to the constituent elements of the support mechanism 26 described above. I will omit it.

As shown in FIGS. 7 and 8, another support mechanism 28 of the transient duct 23 has a structure slightly different from that described above. That is, the support shaft 45 has the flange 45 ₃ formed at the base end thereof fixed to the boss 11 of the outer casing ₁ with the bolt 52. The receiving unit 2 3 ₂ holes 23 ₃ formed transient duct 23, the pressure receiving member 56 having a groove 56 ₁ a cylindrical roller 55 is fitted is rotatably supported via a pin 56 ₂ or protrusions .. On the other hand, the roller 55 is rotatably fitted between a pair of side walls 45 ₂ formed at the tip of the support shaft 45, and is retained by a retainer 57. As a result, the displacement of the support shaft 45 around the axis is absorbed by the rotation of the pressure-receiving member 56 about the pin 56 _1, and the displacement around the axis of the roller 55 is relative to the support shaft 45 relative to the roller 55. It is absorbed by the rotation of the pressure receiving member 56, and further, the displacement of the support shaft 45 in the direction orthogonal to the axis is absorbed by the roller 55 rolling in the groove 56 ₁ of the pressure receiving member 56.

As is apparent from FIG. 2, the pressing force F by the support mechanism 27 is₁Is inclined with respect to the joint surface between the first piece 41 of the scroll 24 and the transient duct 23, and its pressing force F₁Component force F₁′ Receives a reaction force F from the support mechanism 28. ₂ The transient duct 23 is held in a stable state by balancing with.

Next, the axial fixing means for the scroll 24, the back plate 21, and the high pressure turbine shroud 22 will be described with reference to FIGS. 9 to 11. On the rear surface of the metallic base plate 58 attached to the center of the inner casing 18, three roller grooves 58 ₁ extending in the radial direction around the high-pressure turbine shaft 16 are formed at 120 ° intervals (see FIG. 2). ), A roller 60 made of ceramic is housed inside the retainer 59 while being held by the retainer 59. The ceramic back plate 21 arranged so as to face the rear surface of the base plate 58 includes an annular back plate outer 61 and a back plate inner 62 arranged radially inward of the back plate outer 61. A roller groove 61 ₁ with which the roller 60 housed in the roller groove 58 ₁ of the base plate 58 engages is formed at the outer radial end of the front surface of the back plate outer 61. As a result, the back plate 21 is centered with respect to the base plate 58 via the roller 60, and the radial displacement of the base plate 58 and the back plate 21 due to the difference in the coefficient of thermal expansion is absorbed.

Inside the base plate 58, an air passage 58 ₂ communicating with the air passage 19 formed between the outer casing 1 and the inner casing 18 is formed in the radial direction. A pair of partition wall members 63 and 64 are arranged between the inner periphery of the base plate 58 and the compressor rotor 17, and an air chamber 65 defined between the partition wall members 63 and 64 and the air passage 58 of the base plate 58 are provided. ₂ communicate via orifice 58 ₃ . Labyrinths 17 ₁ and 17 ₂ are formed on the partition wall members 63 and 64 and the compressor rotor 17, respectively.

At the lower end of the rear partition member 63, the annular seal plate 66 and the inner periphery of the back plate inner 62 are fastened together by a nut 67. A seal ring 68 is formed between the upper end of the seal plate 66 and the upper end of the back plate inner 62. The seal ring 68 is formed so as to expand outward in the radial direction. The outer periphery of the seal ring 68 is inside the back plate outer 61. By making contact with the circumference, the space between the back plate outer 61 and the back plate inner 62 is sealed.

Thus, the air that has reached the air chamber 65 from the air passage 19 formed between the outer casing 1 and the inner casing 18 through the air passage 58 ₂ and the orifice 58 ₃ of the base plate 58, and the compressor The air reaching the air chamber 65 from the tip of the rotor 17 passes through the labyrinths 17 ₁ and 17 ₂ to cool the high pressure turbine shaft 16, and then acts on the high pressure turbine rotor 20 through the rear surface of the back plate inner 62. Join the combustion gas. Therefore, the back plate inner 62 that comes into contact with the cooling air is kept at a relatively low temperature, and its coefficient of thermal expansion becomes small. On the other hand, the high temperature combustion gas supplied from the scroll 24 directly contacts the back plate outer 61, and the coefficient of thermal expansion thereof becomes large. In this way, the temperature of the back plate 21 differs between the inner side portion and the outer side portion, but since the portion where the temperature is different is divided into separate members of the back plate inner 62 and the back plate outer 61, the back plate 21 is Generation of large thermal stress is prevented. At this time, a gap is generated between the back plate outer 61 and the back plate inner 62 due to the difference in thermal expansion. The gap is sealed by the seal ring 68, and the gap from the high pressure side of the front face of the back plate 21 to the back face of the back plate 21 is increased. Air is prevented from leaking to the low pressure side.

The step portion 22 ₁ formed at the rear end of the high-pressure turbine shroud 22 and the step portion 34 ₁ formed at the front end of the low-pressure turbine duct 34 are loosely spigot-joined, and the outer periphery of the step portion 34 ₁ of the low-pressure turbine duct 34 is annular. The inner circumference of the spring retainer 69 is engaged. The space defined by the high pressure turbine shroud 22, the low pressure turbine duct 34, and the spring retainer 69 is provided with a seal ring 70 having a split opening so as to reduce inward in the radial direction. The inner peripheral surface of the seal ring 70 comes into contact with the outer peripheral surface of the step portion 22 ₁ of the high-pressure turbine shroud 22 by its own elasticity to seal the inner surface of the inner casing 18 on the high-pressure side and the low-pressure turbine duct 34 on the low-pressure side. Due to the pressure difference, it abuts on the front end surface of the low-pressure turbine duct 34 and seals. As a result, the joint can be sealed while absorbing the displacement of the high pressure turbine shroud 22 and the low pressure turbine duct 34 due to thermal expansion.

In the annular space sandwiched between the back plate 21 and the high-pressure turbine shroud 22 in the front-rear direction and sandwiched between the high-pressure turbine rotor 20 and the shroud 24 in the radial direction, a relatively small number, that is, six simple shape Nozzle vanes 25 are provided. Each nozzle vane 25 has its front portion fixed by a pin 71 penetrating the high pressure turbine shroud 22 and its rear portion fixed by another pin 72 engaging with the back plate 21. By simplifying the shape of the nozzle vanes 25 and reducing the number of nozzle vanes in this way, it is possible to reduce the number of parts and facilitate manufacturing while maintaining the same pitch / code ratio as the nozzle vanes of a large number of small size. Moreover, thermal stress can be reduced. Further, since the nozzle vane 25 is sandwiched between the back plate 21 and the shroud 22 and they are connected by the pins 71 and 72, the nozzle vane 25 functions as a link connecting the back plate 21 and the shroud 22, and the back plate 21 It is possible to effectively absorb the displacement due to the thermal expansion of 21 and the shroud 22.

On the other hand, the outer periphery of the back plate 21 and the outer periphery of the high-pressure turbine shroud 22 are supported by the scroll 24 so that the front edge of the inner periphery of the scroll 24 abuts on the outer periphery of the back plate 21 via the detent pin 73. This is done by contacting and pressing the trailing edge with a pressing member 75 made of ceramics urged by a spring 74 compressed between the spring retainer 69 and the spring retainer 69. The pressing members 75 are substantially trapezoidal-shaped members, 24 of which are arranged in the circumferential direction and closely contact each other at the contact surfaces extending in the radial direction, and each of which is biased separately by the spring 74. It The pressing projection 75 ₁ having an arcuate contact surface formed on the outer side in the radial direction of each pressing member 75 presses the inner circumference of the scroll 24, and has the same arcuate contact surface formed on the inner side in the radial direction. The pressing protrusion 75 ₂ presses the back portion of the high pressure turbine shroud 22. At this time, the six pins 71 penetrating the high pressure turbine shroud 22 engage with the six pressing members 75 at corresponding positions to fix the pressing members 75. Further, the other 18 pressing members 75 which are not engaged with the pin 71 are indirectly positioned through the pressing member 75 fixed by the pin 71, and at the same time, both pressing protrusions 75 ₁ and 75 ₂ are attached to the scroll 24. The formed step portion 24 ₂ and the step portion 22 ₂ formed on the high-pressure turbine shroud 22 are brought into contact with each other to be positioned in the radial direction.

Thus, the elastic force of the spring 74 is transmitted through the path of the pressing protrusion 75 _{1 on} the outside of the pressing member 75 → the scroll 24 → the back plate 21, and the elastic force is inside the pressing member 75. Is transmitted through the path of the pressing protrusion 75 ₂ → high pressure turbine shroud 22 → nozzle vane 25 → back plate 21. As a result, even if the back plate 21, the nozzle vane 25, the turbine shroud 22, and the scroll 24 are separately formed in order to achieve the simplification of the shape of parts and the reduction of thermal stress, they are not formed in the pressing member 75. It can be held together by pressing force. At this time, the load of the spring 74 applied to the pressing protrusions 75 ₁ and 75 ₂ on the outer side and the inner side of the pressing member 75 causes the connecting portion of the spring 74 to the pressing member 75, that is, the position of the spring receiving protrusion 75 ₃ to move in the radial direction. By doing so, it is possible to change to any ratio.

Next, the structure of the combustor 12 will be described with reference to FIG. Cylindrical combustor casings 76 and 77 are coaxially welded to the outer casing 1 and the inner casing 18, respectively, and a cylindrical main body casing 78 is attached to a flange 76 ₁ formed at the rear end of the radially outer combustor casing 76. A flange 78 ₁ formed at the rear end is fixed by a bolt 79. As a result, a cooling air passage 80 that communicates with the air passage 19 formed between the outer casing 1 and the inner casing 18 is formed between the combustor casing 77 and the main casing 78 on the radially inner side. A fuel injection nozzle 82 is attached to the tip of the main body casing 78 via a nozzle support member 81, and a burner liner 83 connected to the transient duct 23 is provided in front of the fuel injection nozzle 82. The tip of an igniter 84 supported by the outer casing 1 projects inside the burner liner 83.

Next, the structure of the combustor 12 will be described in more detail with reference to FIGS. 13 to 15. Reverse screws are formed respectively on the fixing member 85 welded to the tip of the inner combustor casing 77 and the tip of the main body casing 78, and an annular liner support member 86 is screwed onto these reverse screws. The inner periphery of the liner support member 86 are three flanges 86 ₁ projecting at 120 ° intervals, three flanges 83 projecting at 120 ° intervals on the rear end outer periphery of the burner liner 83 to the flange 86 _{1 1} is connected to the bayonet. That is, as shown in FIG. 15, after inserting the burner liner 83 into the liner support member 86 by aligning the notch positions of the flange 83 ₁ of the burner liner 83 and the flange 86 ₁ of the liner support member 86, By rotating the burner liner 83 by 120 ° to the position shown in FIG. 14, the burner liner 83 is bayonet-coupled to the liner support member 86. At this time, the rear end of the burner liner 83 is pressed by the blocking member 88 urged by the spring 87 compressed between the burner liner 83 and the nozzle support member 81, and the flange 83 ₁ thereof is located on the rear surface of the flange 86 ₁ of the liner support member 86. Pressed. Then, in order to prevent the rotation of the burner liner 83, the burner liner 83 and the blocking member 88 are connected by a pin 90 such that they cannot rotate relative to each other, and the blocking member 88 and the nozzle support member 81 rotate by a pin 89. Impossiblely linked. With the above structure, the main casing 78 that integrally supports the fuel injection nozzle 82 and the burner liner 83 can be easily attached and detached by simply inserting the main casing 78 from the outside of the outer casing 1 into the combustor casings 76 and 77. It will be possible.

A swirler 91 having a plurality of blades is arranged between the nozzle tip portion 82 ₁ of the fuel injection nozzle 82 and the inner circumference of the base portion of the burner liner 83. A cooling air passage 80 formed between the combustor casing 77 and the main body casing 78 communicates with the inside of the shutoff member 88 through a through hole 78 ₂ and from there, between the fuel injection nozzle 82 and the swirler 91. It communicates with the inside of the burner liner 83 through the annular space. As a result, the low temperature air (about 200 ° C.) introduced from the cooling air passage 80 effectively cools the fuel injection nozzle 82 and the spring 87 to prevent fuel coking (carbonization) and deterioration of the spring 87. be able to. In addition, a part of this low-temperature air is guided from the through hole 82 ₂ to the nozzle tip portion 82 _1, and is also used as blast air for fuel.

On the other hand, the high temperature air (about 800 ° C.) inside the inner casing 18 is swallowed by the swirler 91 through the three openings 92 (see FIGS. 13 and 14) formed between the liner support member 86 and the burner liner 83. Is introduced into the burner liner 83 as primary air. At this time, the partition member 88 prevents mixing of high temperature air and low temperature air. A plurality of air introduction holes 83 ₂ are formed on the outer periphery of the middle portion of the burner liner 83, and the hot air is introduced into the burner liner 83 as secondary air from there. Further, a plurality of other air introduction holes 83 ₃ are formed on the outer periphery of the end portion of the burner liner 83, and the high temperature air is introduced as dilution air from there.

As described above, the transient duct 23 and the burner liner 83 are independently supported in a cantilever manner, and a clearance is formed at the connecting portion between the two. That is, the exit end of the burner liner 83 is a step 83_FourIs formed, and the step portion 83 is formed._FourLoosely fits into the inlet end of the transient duct 23. As a result, even if the transient duct 23 and the burner liner 83 are thermally expanded in the longitudinal direction, the connection between them is prevented from causing thermal stress. As is clear from FIG. 16, the gap δ in the radial direction of the connection part₁Is the axial gap δ₂Smaller than that of the axial direction, and due to thermal expansion, the axial gap δ₂Changes greatly, but the radial clearance δ₁Does not change much. The amount of high temperature air introduced into the transient duct 23 from the joint is relatively small and the radial gap δ₁And the gap δ as described above. ₁ Does not change significantly, so the amount of hot air introduced from the connection is kept substantially constant regardless of temperature. As a result, the step portion 83_FourIt is possible to always introduce a fixed amount of high temperature air into the transient duct 23 via the air passage, and it is possible to prevent the variation of the air-fuel ratio.

[0040] The igniter 84 is fixed by bolts 94 through the fixing member 93 to the boss 1 ₂ formed to the outer casing 1, it can be easily attached to and detached from the outside. A guide member 95 is welded to an opening 18 ₂ of the inner casing 18 through which the igniter 84 passes, and a slider 97 provided on a cylindrical support member 96 through which the igniter 84 is inserted is slidable on the guide member 95. Supported by. A cooling air passage 98 is formed between the support member 96 and the igniter 84, and a seal member 99 is attached to the tip of the cooling air passage 98. As a result, even if each part is displaced by thermal expansion and shakes at the tip of the igniter 84, the shake is absorbed by the slider 97 provided on the support member 96 of the igniter 84 sliding on the guide member 95. To be done. Then, the low temperature air flowing through the air passage 19 between the outer casing 1 and the inner casing 18 is introduced into the cooling air passage 98 inside the support member 96, and efficiently cools the igniter 84.

FIG. 17 shows a modified example of the cooling structure of the igniter 84. In this modified example, the ceramic blocking member 100 slidably mounted on the tip of the supporting member 96 is urged by the spring 101. Contact the outer periphery of the burner liner 83. As a result, the igniter 84 is covered and hot air is prevented from directly contacting the igniter 84.

Next, the operation of the embodiment of the present invention having the above configuration will be described.

The air that has passed through the air cleaner 4 and the silencer 5 and has flowed into the intake passage 6 is compressed to a high pressure by the compressor rotor 17 disposed inside the compressor casing 15 to about 200 ° C., and the outer casing 1 and the inner casing 1 It is sent to the rear via a radial air passage 19 formed between 18. The high-pressure air that has reached the inside of the exhaust housing 3 from the air passages 19 gathers in the upper space of the exhaust housing 3 and then turns to the front to turn to the upper half of the core surface of the rotary heat exchanger 13. Pass the section from back to front. The air thus heated to about 800 ° C. through the heat exchanger 13 flows into the inner space of the inner casing 18 through the opening 29 ₁ formed in the upper portion of the collector housing 29.

A part of the high-temperature air supplied to the inner space of the inner casing 18 is sucked as primary air from the three openings 92 formed between the burner liner 83 and the liner support member 86, and the swirler 91 is discharged. To reach the inside of the burner liner 83. The primary air mixes with the fuel injected from the fuel injection nozzle 82 and burns together with the secondary air flowing into the burner liner 83 from the air inlet port 83 ₂ . The combustion gases were mixed with dilution air introduced from the air introducing hole 83 ₃ is supplied to the scroll 24 through the transient duct 23 blows into the high pressure turbine rotor 20 through between the bottom of six vanes 25 nozzles 32 Be done.

When the high-pressure turbine rotor 20 rotates in this way, the driving force thereof causes the compressor rotor 17 provided on the high-pressure turbine shaft 16 to rotate. The combustion gas that has passed through the high-pressure turbine rotor 20 is blown onto the low-pressure turbine rotor 31 via the low-pressure turbine duct 34 and the variable vanes 33, and rotationally drives the low-pressure turbine shaft 30. The rotation of the low-pressure turbine shaft 30 is decelerated by the speed reducer 14 and taken out from the output shaft 35. After the exhaust gas passing through the low-pressure turbine rotor 31 is collected by the exhaust gas passage 29 ₂ formed in the lower portion of the collector housing 29, passes from the front lower half of the core surface of the rotary heat exchanger 13 back Then, the heat exchanger 13 is heated and discharged to the exhaust duct 8. The heat exchanger 13 heated by the exhaust gas in this way is rotationally driven by the heat exchanger drive motor 40 via the pinion 39 and the ring gear 36, and the heated core surface is sequentially exposed to the passage of the intake air. To heat the intake air.

Since the member in contact with the combustion gas is exposed to a high temperature by the operation of the gas turbine engine G, thermal expansion occurs due to the temperature rise. For example, the scroll 24 mainly thermally expands in the circumferential direction, but since the scroll 24 is divided into four pieces 41 to 44 and abutted at the joint portion, the expansion amount of each piece 41 to 44 is uneven. Even with this, excessive stress is prevented from occurring due to relative displacement of the joint. Further, the thermal expansion of the scroll 24 in the radial direction is absorbed by the expansion and contraction of the support mechanism 26 that supports the outer periphery of the scroll 24, and excessive stress is prevented from occurring.

The transient duct 23 disposed between the combustor 12 and the scroll 24 is also exposed to high temperature. The transient duct 23 has its outlet end portion abuttingly joined to the inlet end portion of the scroll 24, and at the same time, the outer duct The casing 1 is supported by the support mechanisms 27 and 28, and is held in a non-contact state with the burner liner 83. Therefore, not only the generation of thermal stress between the burner liner 83 and the burner liner 83 is prevented, but also the displacement and angle change generated between the transient duct 23 and the outer casing 1 are prevented by the support mechanisms 27 and 28. Can be absorbed.

On the other hand, the back plate 21, the high pressure turbine shroud 22, and the nozzle vane 25, which come into contact with the combustion gas from the scroll 24, are also relatively displaced by thermal expansion. However, each member of the scroll 24, the back plate 21, the high pressure turbine shroud 22, and the nozzle vane 25 is separately formed and axially overlapped with each other, and is pressed by the pressing member 75 urged by the elastic force of the spring 74. Since they are joined together and held together, the displacement is absorbed at the joint and the generation of thermal stress is prevented.

Next, a second embodiment of the present invention will be described with reference to FIGS. 18 is a cross-sectional view of the gas turbine engine corresponding to FIG. 2 described above, FIG. 19 is a cross-sectional view taken along line 19-19 of FIG. 18, FIG. 20 is a cross-sectional view taken along line 20-20 of FIG. 19, and FIG. 21 is a sectional view taken along line 21-21 of FIG.

[0050] This embodiment, each bulging portion 24 ₃ is formed in the outlet end of the four pieces constituting the scroll 24 41-44, enter the bulge portion 24 ₃ of the next piece 41-44 The shape of the scroll 24 is maintained by connecting the spigot to the mouth end. As is apparent from FIG. 20, a slight gap δ ₃ is formed in the circumferential direction in the joint portion of the pieces 41 to 44, and the pieces 41 to 44 are brought into close contact with each other due to thermal expansion and excessive stress is generated. Is prevented.

Instead of holding the scroll 24 from the outer circumference by the support mechanism 26 adopted in the previous embodiment, the scroll 24 is held from the inner circumference by the positioning mechanism 102. That is, a locking flange 24 ₄ is integrally provided on the inner circumference of each of the pieces 41 to 44 that contacts the outer circumference of the high-pressure turbine shroud 22 toward the inner side in the radial direction, and contacts the locking flange 24 ₄ from the rear. The seal ring 103 and the high pressure turbine shroud 22 are axially pressed forward by the pressing member 75 biased by the spring 74.

Two pins 71 penetrating the front part of the two nozzle vanes 25 out of the six nozzle vanes 25 are formed in the engaging flanges 24 ₄ of the back plate 21 and the two pieces 42, 44. It is loosely fitted in the pin hole 24 ₅ and is prevented from coming off by the seal ring 103 (see FIGS. 18 and 21). At this time, since the four pieces 41 to 44 are spigot-engaged with the bulging portion 24 ₃ to retain the shape as a whole, the scroll 24 is attached to the positioning mechanism 102 including the two pins 71 and the engaging flange 24 _4. It is retained inside the inner casing 18. It should be noted that the six pins 72 locked to the rear portions of the six nozzle vanes 25 engage with the six pressing members 75 located at corresponding positions through the high pressure turbine shroud 22, and thereby the nozzle vanes 25 and The pressing member 75 is positioned.

On the other hand, in order to support the back plate 21 with respect to the base plate 58, the roller 60 locked to the roller groove 104 ₁ of the roller supporting member 104 provided on the base plate 58 by the retainer 105 is connected to the roller groove 21 _{1 of the} back plate 21. By engaging with. Similar to the previous embodiment, three rollers 60 are provided radially at intervals of 120 °, whereby the displacement due to thermal expansion of the base plate 58 and the back plate 21 is absorbed, and the concentric holding of both is achieved.

A seal ring 107 urged by a spring 106 provided on the base plate 58 side is in contact with each of the joints of the four pieces 41 to 44 of the scroll 24. The seal ring 109, which is urged by the spring 108 provided on the back plate 21, contacts the back plate 21. As a result, the scroll 24, the back plate 21, the nozzle vane 25, and the high-pressure turbine shroud 22 are elastically imparted by the springs 106, 108, and 74 from the front and rear in the axial direction, so that a difference in mutual thermal expansion amount can be compensated. Are held together.

The partition member 110 arranged between the compressor rotor 17 and the high-pressure turbine rotor 20 is provided with a labyrinth 110 ₁ at the contact portion with the high-pressure turbine shaft 16, and is introduced into the air chamber 111 from the outlet end of the compressor rotor 17. low temperature air cools the high pressure turbine shaft 16 when passing through the labyrinth 1 10 _1.

FIG. 22 shows a third embodiment of the present invention. The four pieces 41 to 44 of the scroll 24 in this embodiment are formed by the bulging portion 24 ₃ as in the second embodiment. They are spigot-bonded to each other with clearance. An annular groove 24 ₆ is recessed in the inner circumference of the scroll 24 facing the outer circumference of the high-pressure turbine shroud 22, and an annular projection 22 ₃ engaging with the annular groove 24 ₆ projects on the outer circumference of the high-pressure turbine shroud 22. Is set up. The pressing member 75 biased by the spring 74 abuts only on the high pressure turbine shroud 22, and the pressing force is transmitted from the high pressure turbine shroud 22 to the scroll 24 via the annular projection 22 ₃ and the annular groove 24 ₆ and the scroll 24. Hold the tool 24 in place. Thus, in this embodiment, the scroll groove 24 ₆ and the annular projection 22 ₃ constitute a positioning mechanism 102 for the scroll 24.

The front portion of the nozzle vane 25 is locked by a pin 71 that engages with the high pressure turbine shroud 22 and the pressing member 75, and the rear portion thereof is locked by a pin 72 that engages with the back plate 21. Further, as in the second embodiment, the back plate 21 is supported by the base plate 58 via the three rollers 60, and the scroll and the outer periphery of the back plate 21 are scrolled in the vicinity of the joints of the pieces 41 to 44. The inner circumference of 24 is supported by seal rings 107 and 109 biased by springs 106 and 108, respectively.

An air passage 58 ₂ communicating with an air passage 19 formed between the outer casing 1 and the inner casing 18 is formed in the base plate 58, and the low temperature air introduced from the air passages 19 and 58 ₂ is a labyrinth 58 ₄ The high pressure turbine shaft 16 as it passes through.

23 to 25 show a fourth embodiment of the present invention. FIG. 23 is a cross sectional view of a gas turbine engine corresponding to FIG. 10, and FIG. 24 is a cross section taken along line 24-24 of FIG. 25 and 25 are cross-sectional views taken along the line 25-25 of FIG.

The scroll 24 of this embodiment has four connecting flanges 24 ₇ projecting from the outlet ends of the pieces 41 to 44, and the connecting flanges 24 ₇ connect the four pieces 41 to 44. The entire shape of the scroll 24 is maintained by joining them to each other. The pressing member 112, which is biased by the elastic force of the plurality of springs 74, is a single annular member, and presses the high pressure turbine shroud 22 by the four hemispherical pressing portions 112 ₁ projecting on the inner periphery thereof. To do.

[0061] with Kakaritome突force 24 ₉ contacting each other on a bonding portion periphery of each piece 41-44 scroll 24 is protruded backward, the pressing portion 112 of the four on the outer periphery of the pressing member 112 ₂ is projected. The pressing portion 112 ₂ of the pressing member 112 is formed in a bifurcated, two locking projections 24 ₉ pieces 41-44 adjacent by the pressing portion ₁₁₂₂ is pressed forward sandwiched. As a result, the outer surfaces of the high pressure turbine shroud 22 and the sealing surfaces 22 ₄ and 24 ₈ formed on the inner surface of the scroll 24 are in close contact with each other. At this time, since the contact surfaces of the pressing portion 112 ₂ and the locking projections 24 ₉ are formed to be inclined in a V shape (see FIG. 25), the pieces 41 to 44 are pressed against each other to maintain the shape. It Thus, the scroll 24 and the high-pressure turbine shroud 22 are simultaneously pressed by the inner and outer pressing portions 112 ₁ and 112 ₂ of the annular pressing member 112, and the pressing force causes the high-pressure turbine shroud 22, the scroll 24, the back plate 21, And the nozzle vane 25 is integrally held.

26 and 27 show a fifth embodiment of the present invention. Similar to the previous fourth embodiment, the pieces 41 to 44 of the scroll 24 of this embodiment have the coupling flange 24. ₇ Are joined together by.

On the inner circumference of the joint portion of each piece 41 to 44 of the scroll 24, a locking protrusion 24 ₁₀ that comes into contact with each other is provided so as to project forward. On the other hand, the four concave portions 58 ₅ formed on the base plate 58 sliding member 113 is fitted in axially movably, it is urged backward by each two spring 1 14. In the recess 113 ₁ formed on the rear surface of the sliding member 113, two gripping claws 115 are arranged in a V shape so as to sandwich the locking projections 24 ₁₀ of the adjacent pieces 41 and 44, and the two claws 115 face each other. The parts are urged by the leaf springs 116 in the directions in which they expand. Both gripping claws 115 are biased in the closing direction by the elastic force of the pressing member 75 from the rear and the elastic force of the sliding member 113 from the front, so that the pieces 41 to 44 of the scroll 24 are integrated. It is held and positioned with respect to the base plate 58.

28 and 29 show a sixth embodiment of the present invention. The four pieces 41 to 44 of the scroll 24 of this embodiment are spigot-joined to each other by the bulging portion 24 _3, but unlike the second embodiment shown in FIG. 18, the spigot joint portion has a clear clearance. It is tightly coupled without having it.

The scroll 24 integrated in this way is held by four support mechanisms 117 from the outer periphery. That is, the substrate 119 which is supported by a leaf spring 118 to the boss 1 ₃ protruding from the outer casing 1 is a sectional quadrant-shaped support rods 120 so as to protrude rearward is fixed. The support rod 120 contacts the outer periphery of the joint portion of the pieces 41 to 44, and presses the scroll 24 inward in the radial direction by the elastic force of the leaf spring 118 to position and fix the scroll 24. According to this embodiment, the scroll 24 is held by applying a pressing force inward in the radial direction from the outer casing 1 as in the first embodiment.

30 to 32 show a seventh embodiment of the present invention. FIG. 30 is a cross-sectional view of a gas turbine engine corresponding to FIG. 2, FIG. 31 is an enlarged view of part 31 of FIG. 32 is a sectional view taken along the line 32-32 of FIG. 32.

The four pieces 41 to 44 of the scroll 24 of this embodiment are joined together by abutting, and at the joint portion, three coupling projections 24 ₁₁ are projected so as to face each other at 120 ° intervals. Is set up. Pin 121 penetrates the coupling projections 24 ₁₁ opposed, movable clamp member which is biased by a fixed clamp member 122 and the spring 123 is slidably supported by the pin 121 provided at an end portion of the pin 121 124 presses the both coupling projections 24 ₁₁ in the circumferential direction of the scroll 24. As a result, the four pieces 41 to 44 are integrally connected, and the outer shape of the scroll 24 is maintained.

33 and 34 show an eighth embodiment of the present invention. FIG. 33 is a view corresponding to FIG. 31, and FIG. 34 is a sectional view taken along line 34-34 of FIG.

In this embodiment as well, similar to the seventh embodiment described above, the pieces 41 to 44 of the scroll 24 are integrally fixed by the elastic force in the circumferential direction. That is, on the four pieces 41 to 44 joined by abutting, three coupling projections 24 ₁₁ each having a small projecting height are provided so as to face each other. The coupling projection 24 ₁₁ is sandwiched between a C-shaped fixed clamp member 125 and a movable clamp member 126, and the elastic force of a spring 123 attached to three pins 121 penetrating both clamp members 125 and 126 is applied. More clamped.

FIG. 35 shows a ninth embodiment of the present invention and corresponds to FIG. 31.

In this embodiment, each of the three bonding projections 24 ₁₁ formed so as to face each other on the four pieces 41 to 44 bonded by abutment is fastened by the heat resistant fiber 127, so that The pieces 41 and 44 are integrated by being given a pressing force in the circumferential direction.

Although the embodiments of the present invention have been described in detail above, the present invention is not limited to the above embodiments, and various modifications can be made without departing from the present invention described in the scope of claims for utility model registration. It is possible to make small design changes.

[0073]

[Effect of the device]

 As described above, according to the first feature of the present invention, the burner liner and the transient duct are independently supported by the casing, and the outlet end of the burner liner and the inlet end of the transient duct are in a non-contact state. Since the burner liner and the transient duct are thermally expanded in the longitudinal direction, the clearance of the connection part is kept almost constant and the dilution introduced from the connection part to the inside of the transient duct. The amount of air can be kept constant. Moreover, since the burner liner and the transient duct do not come into direct contact with each other, thermal stress is prevented from being generated at the connecting portion.

Further, according to the second aspect of the present invention, the transient duct is curved so that the surface formed by the inlet end and the surface formed by the outlet are orthogonal to each other. Not only can it be connected smoothly inside the casing for compact storage, but also the transient duct can be easily manufactured and the processing accuracy can be improved.

According to a third aspect of the present invention, the outlet end of the transient duct is slidably brought into contact with the inlet end of the scroll, and the transient duct is moved from the first supporting means provided on the casing. Since the transient duct and the scroll are coupled by the pressing force applied to the transient duct, it is possible to maintain the transient duct in a stable state without generating excessive stress in the joint portion between the transient duct and the scroll.

According to the fourth aspect of the present invention, since the casing is provided with the second supporting means for giving a reaction force of the component of the pressing force that does not contribute to the coupling of the transient duct and the scroll, the transient duct and the scroll are provided. It is possible to cancel the component of the pressing force that does not directly contribute to the binding of.

According to the fifth feature of the present invention, the second support means is provided with a joint means capable of absorbing relative movement and relative angular displacement of the casing and the transient duct. A stable pressing force can always be applied regardless of thermal expansion.

[Brief description of drawings]

FIG. 1 is a vertical sectional view of a gas turbine engine.

FIG. 2 is a sectional view taken along line 2-2 of FIG.

FIG. 3 is an enlarged view of a main part of FIG.

4 is an enlarged view of part 4 of FIG.

5 is an enlarged view of part 5 of FIG.

FIG. 6 is an enlarged view of a main part of FIG.

FIG. 7 is an enlarged view of a main part of FIG.

8 is a sectional view taken along line 8-8 of FIG.

9 is an enlarged view of a main part of FIG.

10 is a view taken along the line 10-10 of FIG.

11 is a sectional view taken along line 11-11 of FIG.

FIG. 12 is an enlarged view of a main part of FIG.

FIG. 13 is an enlarged view of a main part of FIG.

14 is a sectional view taken along line 14-14 of FIG.

FIG. 15 is an explanatory diagram of an operation corresponding to FIG.

16 is an enlarged view of part 16 in FIG.

FIG. 17 is a view showing a modified example of the igniter mounting portion.

FIG. 18 is a cross-sectional view of a gas turbine engine according to a second embodiment of the present invention.

19 is a sectional view taken along line 19-19 of FIG.

20 is a sectional view taken along line 20-20 of FIG.

21 is a cross-sectional view taken along line 21-21 of FIG.

FIG. 22 is an enlarged view of a main part of a gas turbine engine according to a third embodiment of the present invention.

FIG. 23 is a cross-sectional view of a gas turbine engine according to a fourth embodiment of the present invention.

24 is a sectional view taken along line 24-24 of FIG.

25 is a sectional view taken along line 25-25 of FIG.

FIG. 26 is an enlarged view of a main part of a gas turbine engine according to a fifth embodiment of the present invention.

27 is a sectional view taken along line 27-27 of FIG.

FIG. 28 is a cross-sectional view of a gas turbine engine according to a sixth embodiment of the present invention.

29 is a sectional view taken along line 29-29 of FIG. 28.

FIG. 30 is a cross-sectional view of a gas turbine engine according to a seventh embodiment of the present invention.

31 is an enlarged view of part 31 in FIG. 30.

32 is a sectional view taken along line 32-32 of FIG.

FIG. 33 is a view showing a joint portion of a scroll according to an eighth embodiment of the present invention.

34 is a sectional view taken along the line 34-34 in FIG. 33.

FIG. 35 is a view showing a joint portion of a scroll according to a ninth embodiment of the present invention.

[Explanation of symbols]

1 ... Outer casing (casing) 23 ... Transient duct 24 ... Scroll 27 ... Support mechanism (first support means) 28 ... Support mechanism (second support means) 55 ... Roller (Coupling means) 56 ... Pressure receiving member (coupling means) 83 ... Burner liner F ₁ ... Pressing force F ₁ '... Component of pressing force F ₂ ... Reaction force

Claims (5)

[Scope of utility model registration request] 1. A gas turbine engine in which a burner liner (83), a transient duct (23) and a scroll (24) are sequentially connected inside a casing (1), the burner liner (83) and the transient duct being provided. (23) are independently supported by the casing (1), and the outlet end of the burner liner (83) and the inlet end of the transient duct (23) are connected to each other in a non-contact state so as to overlap each other. A gas turbine engine characterized by. 2. The transient duct (23),
The gas turbine engine according to claim 1, wherein a surface formed by the inlet end portion and a surface formed by the outlet end portion are curved so as to be orthogonal to each other. 3. An outlet end of the transient duct (23) slidably abuts on an inlet end of the scroll (24), and a transient is provided from a first supporting means (27) provided on the casing (1). With the pressing force (F ₁ ) applied to the duct (23), the transient duct (2
Gas turbine engine according to claim 2, characterized in that the scroll (3) and the scroll (24) are combined. 4. A _second force giving a reaction force (F ₂ ) of the component (F ₁ ′) of the pressing force (F ₁ ), which does not contribute to the coupling of the transient duct (23) and the scroll (24).
Gas turbine engine according to claim 3, characterized in that the supporting means (28) are provided on the casing (1). 5. The second supporting means (28) comprises joint means (55, 56) capable of absorbing relative movement and relative angular displacement of the casing (1) and the transient duct (23). The gas turbine engine according to claim 4.