WO2018196198A1 - 用于燃气涡轮的叶型管式喷嘴 - Google Patents

用于燃气涡轮的叶型管式喷嘴 Download PDF

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Publication number
WO2018196198A1
WO2018196198A1 PCT/CN2017/094921 CN2017094921W WO2018196198A1 WO 2018196198 A1 WO2018196198 A1 WO 2018196198A1 CN 2017094921 W CN2017094921 W CN 2017094921W WO 2018196198 A1 WO2018196198 A1 WO 2018196198A1
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WIPO (PCT)
Prior art keywords
section
circular
nozzle
outlet
airflow
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/CN2017/094921
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English (en)
French (fr)
Inventor
吕剑波
罗华玲
胡书珍
潘贤德
刘国峰
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AECC Commercial Aircraft Engine Co Ltd
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AECC Commercial Aircraft Engine Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by AECC Commercial Aircraft Engine Co Ltd filed Critical AECC Commercial Aircraft Engine Co Ltd
Priority to CA3062856A priority Critical patent/CA3062856C/en
Priority to EP17907287.1A priority patent/EP3617480B1/en
Priority to KR1020197033529A priority patent/KR102364454B1/ko
Priority to JP2020509137A priority patent/JP2020518764A/ja
Priority to US16/609,044 priority patent/US11028708B2/en
Priority to RU2019136870A priority patent/RU2729589C1/ru
Publication of WO2018196198A1 publication Critical patent/WO2018196198A1/zh
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/128—Nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/14—Two-dimensional elliptical
    • F05D2250/141—Two-dimensional elliptical circular
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/14—Preswirling
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to a pre-rotating nozzle for a pre-spin cooling system for an aviation gas turbine engine.
  • the high-pressure turbine rotor air is usually vented by the compressor and provided after the combustion chamber.
  • the pre-rotation nozzle is usually used to turn the airflow, reduce the relative temperature of the cold air and reduce the consumption of cold air, thereby improving the cooling effect of the high-pressure turbine and reducing the fuel consumption of the engine.
  • the pre-spin nozzle design mainly adopts two types: circular duct type and vane type.
  • Straight-circular pipeline pre-spin nozzles are the first to be applied with fewer channels, better exit airflow angle characteristics, and easier manufacturing.
  • straight circular pipe type or a flared pipe type that expands the inlet pipe diameter (Prior Art 1)
  • its lower cooling performance becomes more and more difficult. accept.
  • the leaf shape is the most ideal structure for the flow of the twisted airflow known to man.
  • the blade type pre-spin nozzle requires a number of channels (equal to the number of blades) that is multiplied by a circular ducted pre-spin nozzle to achieve a turning of the airflow.
  • the blade height of the blade type pre-spin nozzle is usually very low (3 to 4 mm), which results in its smaller aspect ratio, which limits the cooling performance of the blade type pre-rotation nozzle; more importantly, it also greatly increases The manufacturing difficulty.
  • the blade type pre-spin nozzle is usually obtained by welding or casting. The number of blades and the small blade height make the welding production complicated and expensive, and the casting production yield is low, so the blade type pre-rotating nozzle It is more difficult in engineering applications.
  • a leaf-tube nozzle for a gas turbine includes an inlet section, a constriction section, and an outlet section that are sequentially joined in a flow direction of the airflow, the inlet section being a section of an annular passage, the constricted section including a plurality of airflow passages separated by a plurality of blades, each of the airflow passages being surrounded by a peripheral wall surface, an inner peripheral wall surface, a suction surface of one of the two adjacent blades, and a pressure surface of the other adjacent blade
  • the inlet of the air flow passage has a fan-shaped cross section; as seen in the flow direction of the air flow, for each of the air flow passages, the fan-shaped cross section gradually transitions into a circular cross section from the inlet to the outlet of the air flow passage, wherein
  • the two adjacent vanes are disposed to dominate the turning of the airflow in the circumferential direction of the nozzle, and the outer peripheral wall surface and the inner peripheral wall surface are disposed to dominate the turning of the airflow in the radi
  • the outlet section is a spiral tube having a spiral axis, the spiral passes through a center of the circular section, a tangent of the spiral at a center of the circular section and the The normal vector of the circular section is parallel.
  • the axial distance between the center of the circular section and the outlet of the circular duct along the axis of the circular duct is the axial length of the circular duct, in the 0.1 to 5 times the diameter of the circular cross section.
  • the outlet section is a straight tube with a straight line axis, the axis passing through the circular shape of the circular cross section and parallel to the normal vector of the circular cross section.
  • the inlet section is a section of an annular passage.
  • the circular duct is an axis with a straight line of the projection line
  • the projection line is a projection of the straight line on a plane of revolution on which the center of the initial circular section of the circular duct is located.
  • the turning surface is described above
  • the center of the initial circular section to the perpendicular of the axis of the blade-type nozzle is a diameter and a cylindrical surface extending parallel to the axial direction of the blade-type nozzle.
  • the airfoil tubular nozzle is used in a pre-spin cooling system in an aeroengine high pressure turbine that folds cold air into a high pressure turbine rotor blade root.
  • the engineering design of the blade type pre-spin nozzle has the requirements of increasing the blade pitch, reducing the number of blades, and increasing the blade height to reduce the manufacturing difficulty.
  • the blade type pre-spin nozzle can not improve the blade height without degrading the performance, but the round tube type has the advantages of suitable size and easy production; at the same time, the blade type design is very difficult when the blade number is significantly reduced, and the blade performance is seriously degraded.
  • the round tube itself has the advantage of a small number of channels, but its performance is poor.
  • the main reason for the poor aerodynamic performance of the round tube pre-rotation nozzle is that the airflow transition in the inlet section is too large, and there is a large separation flow. Even the flared tubular pre-rotation nozzle has a limited increase in aerodynamic performance, which is far less than that. Excellent blade performance.
  • the leaf-shaped tubular nozzle according to the present invention satisfies the pre-rotation nozzle having the advantages of having a small number of passages, being easy to manufacture, and the like, and at the same time being close to the performance of the blade-type pre-rotating nozzle, and the nozzle can be Significantly reduce the number of blades with reduced performance.
  • the leaf-shaped control fan-shaped flow passage section is gradually and smoothly contracted into a circular tube shape, and a circular pipe of a length is maintained to the outlet, and the diameter of the circular pipe does not change along the axis, thereby realizing the fusion design of the blade and the circular pipe.
  • a new type of leaf type tubular pre-spin nozzle is satisfies the pre-rotation nozzle having the advantages of having a small number of passages, being easy to manufacture, and the like, and at the same time being close to the performance of the blade-type pre-rotating nozzle, and the nozzle can be Significantly reduce the number of blades with reduced performance.
  • the blade deflects the airflow with a lower aerodynamic loss, the circular duct stabilizes the airflow exit direction, and the blade and the circular duct have a smooth transition; and the leaf-type pre-rotation nozzle transitions from the scalloped surface to the scalloped surface, and the flow passage Has been shrinking.
  • the circular tube of the leaf type tubular pre-rotating nozzle is designed based on the circular tube type pre-rotating nozzle, which significantly reduces the number of blades and increases the height of the blade outlet height.
  • the flow path of the airfoil turning function of the airfoil type pre-rotating nozzle according to the present invention is designed based on the blade type pre-rotating nozzle, and the flow path section is smoothly contracted along the blade shape into a circular tube shape, overcoming the leaf type hole pre-prevention.
  • the thickness near the leading edge of the rotary nozzle is too large, and the leading edge is flat and blunt, which avoids the attenuation of the performance under a slightly lower Reynolds number condition, so that the leaf-type tubular pre-spin nozzle has a performance level and stable performance similar to the blade type.
  • Figure 1 is a perspective view of a duct-type nozzle according to the present invention, wherein its outlet side is shown in a transverse section.
  • FIG. 2 is a front elevational view of a leaf-tube nozzle in accordance with the present invention, with its inlet side shown in a transverse section.
  • Figure 3 is a rear elevational view of a leaf-tube nozzle in accordance with the present invention with its outlet side shown in a transverse cross-section.
  • FIG. 4 is a side cross-sectional view of a leaf-tube nozzle in accordance with the present invention.
  • Figure 5 is a side view of a 50%-leaf-turn surface segment of a leaf-tube nozzle according to the present invention.
  • Figure 6 is a perspective view of a 50%-leaf-turn surface split body of a leaf-tube nozzle according to the present invention.
  • Fig. 7 is a perspective view of a 50%-leaf-turn surface split body of a leaf-tube nozzle according to another embodiment of the present invention.
  • Fig. 8 is a perspective view showing a 50%-leaf-turn surface split body of a leaf-tube nozzle according to still another embodiment of the present invention.
  • FIG. 1 to 6 show an embodiment of the present invention.
  • Figure 7 shows another embodiment of the invention.
  • Figure 8 shows a further embodiment of the invention.
  • the leaf-tube nozzle 101 includes a peripheral side wall 110, an inner peripheral side wall 111, a plurality of vanes 105, and a plurality of circular ducts 104.
  • the outer peripheral side wall 110 and the inner peripheral side wall 111 are annular members, and the inner peripheral side wall is located in the outer peripheral side wall 110.
  • the plurality of vanes 105 are connected and fixed between the outer peripheral side wall 110 and the inner peripheral side wall 111, and a plurality of circular shapes.
  • the duct 104 is also connected and fixed between the outer peripheral side wall 110 and the inner peripheral side wall 111.
  • the blade shape of the blade 105 can be provided in accordance with the blade of an existing blade type pre-rotating nozzle including a leading edge, a trailing edge, a pressure face and a suction face, a base end and a tip end.
  • the base end is connected and fixed to the outer peripheral surface of the inner peripheral side wall 111, and the top end is connected and fixed to the inner peripheral surface of the outer peripheral side wall 110.
  • the front edge is located at the inlet of the air flow passage described later, and the rear edge is located at the outlet of the air flow passage.
  • the leaf tube nozzle 101 includes an inlet section 108, a constricted section 107, and an outlet section 106.
  • the preferred solid form of the leaf-type tubular nozzle 101 can be a cast monomer, and the inlet section 108, the constricted section 107, and the outlet section 106 can be a description of the different geometrical positions of the casting monomer.
  • the inlet section 108 and the outlet section 106 rely on the constricted section 107 To achieve a smooth transition, thus forming a complete continuous flow channel.
  • the inlet section 108 is a length of annular passage defined between the peripheral side wall 110 and the inner peripheral side wall 111 that can be used to mount the airfoil tubular nozzle 101 in the outer wall of the casing in the combustion chamber.
  • the constricted section 107 is surrounded by the outer peripheral side wall 110, the inner peripheral side wall 111 and the plurality of vanes 105, wherein the two adjacent vanes 105 are surrounded by the inner wall surface of the outer peripheral side wall 110 and the outer wall surface of the inner peripheral side wall 111.
  • the air flow passage, the plurality of air flow passages are distributed along the entire circumference of the airfoil nozzle 101.
  • an air flow passage is taken as an example, and the description is also suitable for other air flow passages.
  • the inlet 102 of the air flow passage has a fan shape, and the sector shape herein is understood to be defined by an arc shape defined by the outer peripheral side wall 110 and the inner peripheral side wall 111, respectively, and a suction surface 112 of one of the vanes 105, respectively.
  • the straight line and the line defined by the pressure surface 113 of the adjacent blade intersect to form a shape.
  • the outlet of the air flow passage is a circular section 103.
  • the shape from the inlet 102 to the outlet 103 is tapered, and on the other hand, between the outer peripheral side wall 110 and the inner peripheral side wall 111.
  • the distance is gradually narrowed.
  • the distance between the opposite suction surface 112 and the pressure surface 113 is gradually narrowed, and the cross-sectional shape of the air flow passage is gradually contracted from the sector shape to the circular shape.
  • the vane 105 is configured such that the airflow of the main airflow passage is turned in the circumferential direction of the vane nozzle 101, and the outer peripheral side wall 110 and the inner peripheral side wall 111 are arranged to dominate the airflow in the radial direction of the vane nozzle 101. Transition.
  • the outlet section 106 provides a circular duct 104 having a diameter that does not vary along the axis.
  • the circular duct 104 has a helix 109 as an axis and the helix 109 is circular.
  • the tangent of the helix 109 at the center of the circular section 103 is parallel to the normal of the circular section 103.
  • the axial distance between the center of the circular section 103 and the exit of the circular duct 104 is the axial length of the circular duct 104 and may be between 0.1 and 5 times the diameter of the circular section 103.
  • the number of blades of the constricted section 107 can be from 8 to 40, and in the embodiment shown in the figure, there are 26 blades 105.
  • the foregoing embodiment adopts the blade shape of two adjacent blades 105 to control the fan-shaped flow passage section to gradually shrink into a circular tube shape, and maintain a length of the circular pipe 104 to the outlet of the nozzle, and the diameter of the circular pipe 104 is not along the axis.
  • the change thus realizes a novel leaf-type tubular pre-rotation nozzle in which the blade 105 and the circular duct 104 are fused.
  • the vanes 105 deflect the airflow with a lower aerodynamic loss, and the circular ducts 104 stabilize the airflow exit direction and a smooth transition between the vanes 105 and the circular ducts 104.
  • the circular duct 104 of the leaf-type tubular pre-spin nozzle shown in the figure is designed based on a circular tube pre-spin nozzle
  • the effect is that the number of blades cannot be significantly reduced without degrading performance.
  • the number of blades and the larger blade height dimension overcome the shortage of the blade type pre-spin nozzle and its modification, which can reduce the manufacturing difficulty and improve the yield.
  • the airflow passage before the circular duct 104 of the airfoil tubular pre-rotation nozzle according to the present invention is designed based on the blade type pre-spin nozzle, and the flow passage section is smoothly contracted along the blade type into a circle.
  • the shape of the tube does not cause problems such as excessive thickness near the leading edge of the leaf-type pre-spin nozzle and blunt leading edge.
  • the leading edge of the leaf-type pre-rotating nozzle is blunt and thick, so that the nozzle performance is severely attenuated under a slightly lower Reynolds number condition, while the leaf-type tubular pre-rotating nozzle has similar performance level and stable performance as the blade type.
  • Fig. 7 shows another embodiment of the present invention, and the description of the same technical content is selectively omitted in this embodiment.
  • the description of the omitted portions reference may be made to the foregoing embodiments, and the detailed description is not repeated herein.
  • outlet section 206 is a circular duct 204 having a diameter that does not vary along the axis, the circular duct 204 having the line 209 as the axis and the straight line 209 crossing the circular section 203.
  • FIG. 8 shows an alternative embodiment of the present invention, which selectively omits the description of the same technical content.
  • the present embodiment is different from that shown in FIGS. 1 to 6 in that the outlet section 306 is a circular duct 304 whose diameter does not vary along the axis, and the circular duct 304 is a projection line 310 of the straight line 309. Axis.
  • the projection line 310 is a projection of a straight line 309 on a plane of revolution on which the center of the circular section 303 is centered, and the plane of revolution is a diameter from the center of the circular section 303 to the axis of the axis of the leaf-shaped nozzle 101, and is parallel to The axially stretched cylindrical surface of the leaf-shaped tubular nozzle 101.
  • the flow coefficient range of the same type of pre-spin nozzle at a pressure ratio of 1.6 is as follows:

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

一种用于燃气涡轮的叶型管式喷嘴（101），包括入口段（108）、收缩段（107）和出口段（106）。其中，入口段（108）为一段环形通道，收缩段（107）包括由多个叶片（105）分隔开的多个气流流通通道，每个气流流通通道由外周壁面（110）、内周壁面（111）、两相邻叶片（105）之一的吸力面以及两相邻叶片（105）另一个的压力面围成，该气流流通通道的入口（102）呈扇形截面；对于每个气流流通通道，顺着气流流动方向看，从该气流流通通道的入口（102）到出口（103），扇形截面逐步光滑过渡为圆形截面。出口段（106）包括对应各个该气流流通通道的出口（103）分别连接的、直径不沿轴线变化的圆形管道（104）。相对于叶型孔式喷嘴，该叶型管式喷嘴可以在不降低性能的前提下显著减少叶片数。

Description

用于燃气涡轮的叶型管式喷嘴 技术领域
本发明涉及航空燃气涡轮发动机预旋冷却系统的预旋喷嘴。
背景技术
在航空发动机的高压涡轮部件设计中，高压涡轮转子冷气通常是由压气机引气，途径燃烧室后提供的。冷气输运到高压涡轮转动盘前时，因盘转动会造成冷气的相对总温增大，不利于冷却高压涡轮。在工程设计中，通常采用预旋喷嘴来转折气流，减小冷气相对总温，降低冷气消耗量，从而提升高压涡轮冷却效果，并降低发动机耗油率。
在已经服役的国内外发动机机型和公开材料中，预旋喷嘴设计主要采用了圆形管道式和叶片式两大类型。
直圆形管道式预旋喷嘴以较少的通道数，更好的出口气流角特性，生产制造更易实现等优点得到最先应用。然而随着航空发动机循环参数的逐步提高，无论是直圆形管道式，还是通过扩大入口管径的扩口管式(现有技术1)，其较低的降温性能都变得越来越难以接受。
叶型是人类已知的转折气流流向最理想的结构，研究人员发现采用叶片式预旋喷嘴可以实现比圆形管道式更好的降温性能。然而叶片式预旋喷嘴需要采用比圆形管道式预旋喷嘴成倍增加的通道数(等于叶片数)来实现气流的转折。同时叶片式预旋喷嘴的叶片高度通常很低(3～4mm),这一方面造成了其较小的展弦比，限制了叶片式预旋喷嘴的降温性能；更重要的是还极大地增加了生产制造难度。在工业生产中，叶片式预旋喷嘴通常采用焊接或者铸造方式获得，数量较多的叶片数和较小的叶片高度使得焊接生产复杂又昂贵，铸造生产则成品率低下，故叶片式预旋喷嘴在工程应用中难度较大。
有研究人员提出了叶型孔式预旋喷嘴方案(现有技术2)，通过将叶型的吸力面和压力面分离一定间距来增厚叶片，从而减少单个流通通道的喉部宽度。设计时保持总喉部面积不改变，则可提升叶片高度。这一技术方案可在一定范围内解决叶片式预旋喷嘴叶片高度小的缺点，但是通过增大吸力面和压力面间距来增厚叶型会使得叶片前缘厚度过大、几何平钝。气流在大厚度、平度的前缘附近绕流流动时，会产生更大 的气动损失，尤其是工作在雷诺数Re<4×〖10〗^5的工况时性能会衰减至扩口管式预旋喷嘴的水平，性能不及叶片式预旋喷嘴稳定。同时这种叶型孔式预旋喷嘴(现有技术2)无法在保持性能水平不下降的前提下显著减少叶片数，若将这种叶型孔式预旋喷嘴(现有技术2)应用于生产，其将仍然面临着与叶片式预旋喷嘴相同的技术困难。
发明内容
本发明的目的在于提供一种用于燃气涡轮的叶型管式喷嘴，相对于叶型孔式喷嘴，可以在不降低性能的前提下显著减少叶片数。
根据本发明的用于燃气涡轮的叶型管式喷嘴，其包括顺着气流流动方向依次相接的入口段、收缩段和出口段，所述入口段为一段环形通道，所述收缩段包括由多个叶片分隔开的多个气流流通通道，每个所述气流流通通道由外周壁面、内周壁面、两相邻叶片之一的吸力面以及所述两相邻叶片另一个的压力面围成，该气流流通通道的入口呈扇形截面；顺着气流流动方向看，对于每个所述气流流通通道，从该气流流通通道的入口到出口，扇形截面逐步光滑过渡为圆形截面，其中所述两相邻叶片设置成主导气流在该喷嘴的圆周方向的转折，而所述外周壁面、所述内周壁面设置成主导气流在该喷嘴的半径方向的转折；所述出口段包括对应各个该气流流通通道的出口分别连接的、直径不沿轴线变化的圆形管道。
在一实施例中，所述出口段为以螺旋线为轴线的螺旋管，所述螺旋线过所述圆形截面的圆心，所述螺旋线在所述圆形截面圆心处的切线与所述圆形截面的法向量平行。
在一实施例中，所述圆形截面的圆心与所述圆形管道的出口之间的沿所述圆形管道的轴线的轴向距离，为所述圆形管道的轴向长度，处在0.1～5倍于所述圆形截面的直径之间。
在一实施例中，所述出口段为以直线为轴线的直管，所述轴线通过所述圆形截面的圆形，并平行于所述圆形截面的法向量。
在一实施例中，所述入口段为一段环形通道。
在一实施例中，所述圆形管道以一直线的投影线为轴线，所述投影线为所述直线在所述圆形管道的起始圆形截面圆心所在的回转面上的投影，所述回转面是以所述起 始圆形截面的圆心至该叶型管式喷嘴的轴心的垂线为直径且沿平行于该叶型管式喷嘴的轴向拉伸的圆柱面。
在一实施例中，所述叶型管式喷嘴用于航空发动机高压涡轮中的预旋冷却系统，将冷气折转后再送入高压涡轮转子叶根。
如前所述，叶片式预旋喷嘴的工程设计中有增大叶片间距、减少叶片数、提高叶片高度来降低生产制造难度的要求。叶片式预旋喷嘴无法在不降低性能时提高叶片高度，但圆管式具有尺寸合适、易于生产实现的优点；同时叶片式在显著减少叶片数时叶型设计十分困难，叶片性能下降严重，而圆管式本身具有通道数少的优点，但性能却较差。圆管式预旋喷嘴气动性能较差的主要原因是其在入口段气流转折过大，会有较大的分离流动存在，即使是扩口管式预旋喷嘴其气动性能仍然提升有限，远不及叶片式性能优异。
根据本发明的叶型管式喷嘴满足具有通道数少、易于生产制造等优点，同时又与叶片式预旋喷嘴性能处在相近水平的预旋喷嘴，相对于叶型孔式喷嘴，可以在不降低性能的前提下显著减少叶片数。其采用叶型控制扇形流道截面逐步光滑地收缩为圆管形状，并保持一段长度的圆形管道至出口，圆形管道的直径不沿轴线变化，从而实现了叶片和圆形管道融合设计的新型叶型管式预旋喷嘴。叶片以较低的气动损失转折气流，圆形管道则可稳定气流出口方向，叶片与圆形管道之间光滑过渡；而叶型孔式预旋喷嘴是从扇形面过渡到扇形面，并且流道一直在收缩。叶型管式预旋喷嘴的圆形管道基于圆管式预旋喷嘴进行设计，显著降低了叶片数，提高了叶片出口高度尺寸。根据本发明的叶型管式预旋喷嘴起到气流转折功能的流道则是基于叶片式预旋喷嘴进行设计的，流道截面沿叶型光滑收缩为圆管形状，克服了叶型孔预旋喷嘴前缘附近厚度过大、前缘平钝等不足，避免了出现性能在稍低雷诺数工况下衰减，使得叶型管式预旋喷嘴具有了与叶片式相近的性能水平和性能稳定工作范围。
附图说明
本发明的上述的以及其他的特征、性质和优势将通过下面结合附图和实施例的描述而变得更加明显，其中：
图1为根据本发明的叶型管式喷嘴的立体图，其中其出口侧以横向剖面被示出。
图2为根据本发明的叶型管式喷嘴的主视图，其中其入口侧以横向剖面被示出。
图3为根据本发明的叶型管式喷嘴的后视图，其中其出口侧以横向剖面被示出。
图4为根据本发明的叶型管式喷嘴的侧向半剖视图。
图5为根据本发明的叶型管式喷嘴的50％叶高回转面分割体侧视图。
图6为根据本发明的叶型管式喷嘴的50％叶高回转面分割体立体图。
图7为根据本发明的另一实施例的叶型管式喷嘴的50％叶高回转面分割体立体图。
图8为根据本发明的又一实施例的叶型管式喷嘴的50％叶高回转面分割体立体图。
具体实施方式
下面结合具体实施例和附图对本发明作进一步说明，在以下的描述中阐述了更多的细节以便于充分理解本发明，但是本发明显然能够以多种不同于此描述的其它方式来实施，本领域技术人员可以在不违背本发明内涵的情况下根据实际应用情况作类似推广、演绎，因此不应以此具体实施例的内容限制本发明的保护范围。
需要注意的是，附图均仅作为示例，其并非是按照等比例的条件绘制的，并且不应该以此作为对本发明实际要求的保护范围构成限制。
图1至图6显示了本发明的一实施例。图7显示了本发明的另一实施例。图8显示了本发明的又一实施例。
如图1至图6所示，在本发明的一实施例中，叶型管式喷嘴101包括外周侧壁110、内周侧壁111、多个叶片105以及多个圆形管道104。外周侧壁110和内周侧壁111为环形构件，内周侧壁位于外周侧壁110内，多个叶片105连接并固定在外周侧壁110、内周侧壁111之间，多个圆形管道104也连接固定在外周侧壁110、内周侧壁111之间。叶片105的叶型可以按照已有的叶片式预旋喷嘴的叶片来提供，其包括前缘、后缘、压力面和吸力面、基端和顶端。基端与内周侧壁111的外周面连接固定，顶端与外周侧壁110的内周面连接固定，前缘位于后述气流流通通道的入口，后缘位于气流流通通道的出口。
叶型管式喷嘴101包括入口段108、收缩段107、出口段106。叶型管式喷嘴101的优选的实体型态可以是一个铸造单体，入口段108、收缩段107、出口段106可以是对该铸造单体不同几何位置的描述。入口段108与出口段106依靠收缩段107 来实现光滑过渡，从而形成了一个完整连续的流通通道。入口段108为外周侧壁110和内周侧壁111之间限定的一段环形通道，其可以用于将叶型管式喷嘴101安装在燃烧室内机匣外壁。收缩段107由外周侧壁110、内周侧壁111以及多个叶片105共同围成，其中两相邻叶片105与外周侧壁110的内壁面、内周侧壁111的外壁面共同围成一个气流流通通道，多个气流流通通道沿叶型管式喷嘴101的整个周向分布。在后面以一个气流流通通道为例进行说明，其描述也适合于其他的气流流通通道。
如图2所示，气流流通通道的入口102呈扇形，此处所述扇形可以理解成由外周侧壁110、内周侧壁111分别限定的弧形分别与其中一个叶片105的吸力面112限定的直线、相邻叶片的压力面113限定的直线相交形成的形状。
如图4所示，气流流通通道的出口为圆形截面103。
如图1至图6所示，对于一个气流流通通道，从气流流动的方向来看，从入口102到出口103为渐缩的形状，一方面，外周侧壁110和内周侧壁111之间的距离逐渐收窄，另一方面，相对的吸力面112和压力面113之间的距离也逐渐收窄，并且，气流通道的截面形状从扇形形状逐渐收缩为圆形。叶片105配置成主导气流流通通道的气流在叶型管式喷嘴101的圆周方向的转折，而外周侧壁110和内周侧壁111则配置成主导气流在叶型管式喷嘴101的半径方向的转折。
如图5和图6所示，对应于每一个气流流通通道，出口段106提供一段直径不沿轴线变化的圆形管道104，圆形管道104以螺旋线109为轴线，螺旋线109过圆形截面103的圆心。螺旋线109在圆形截面103圆心处的切线与圆形截面103的法向量平行。
圆形截面103圆心与圆形管道104出口间的轴向距离，为圆形管道104的轴向长度，可处在0.1～5倍于圆形截面103的直径之间。
收缩段107的叶片数可为8～40个，在如图所示的实施例中为26个叶片105。
前述实施例采用两相邻叶片105的叶型来控制扇形流道截面逐步光滑地收缩为圆管形状，并保持一段长度的圆形管道104至喷嘴的出口，圆形管道104的直径不沿轴线变化，从而实现了叶片105和圆形管道104融合设计的新型叶型管式预旋喷嘴。叶片105以较低的气动损失转折气流，圆形管道104则可稳定气流出口方向，叶片105与圆形管道104之间光滑过渡。
如图所示的叶型管式预旋喷嘴的圆形管道104是基于圆管式预旋喷嘴进行设计 的，显著降低了叶片数，提高了叶片高度尺寸，相对于叶型孔式预旋喷嘴具有明显的优点，因为叶型孔式预旋喷嘴只能通过减小单通道喉部宽度达到提高叶片高度的效果，无法在不降低性能的前提下显著减少叶片数。根据前述实施例的叶型管式预旋喷嘴较少的叶片数、更大的叶片高度尺寸，克服了叶片式预旋喷嘴及其改型的不足，可以降低生产制造难度，提高成品率。
继续参照图1到图6，根据本发明的叶型管式预旋喷嘴的圆形管道104之前的气流流通通道是基于叶片式预旋喷嘴进行设计的，流道截面沿叶型光滑收缩为圆管形状，从而不会出现叶型孔式预旋喷嘴的前缘附近厚度过大、前缘平钝等问题。叶型孔式预旋喷嘴的前缘平钝、厚度大使得喷嘴性能在稍低雷诺数工况下性能衰减严重，而叶型管式预旋喷嘴则具有与叶片式相近的性能水平和性能稳定工作范围。
图7示出了本发明的另一实施例，本实施例选择性地省略了相同技术内容的说明。关于省略部分的说明可参照前述实施例，本实施例不再重复赘述。
如图7所示的实施例与前述实施例不同点在于，出口段206为一段直径不沿轴线变化的圆形管道204，圆形管道204以直线209为轴线，直线209过圆形截面203的圆心，平行于圆形截面203的法向量。
图8示出了本发明的另一实施例中，本实施例选择性地省略了相同技术内容的说明。关于省略部分的说明可参照前述实施例，本实施例不再重复赘述。如图8所示，本实施例与图1至图6所示的不同点在于，出口段306为一段直径不沿轴线变化的圆形管道304，圆形管道304以直线309的投影线310为轴线。投影线310为直线309在圆形截面303圆心所在的回转面上的投影，所述回转面是以圆形截面303圆心至叶型管式喷嘴101的轴心的垂线为直径且沿平行于叶型管式喷嘴101的轴向拉伸的圆柱面。
根据发明人的试验，同类型预旋喷嘴在压比1.6附近的流量系数范围列表如下：
Figure PCTCN2017094921-appb-000001
Figure PCTCN2017094921-appb-000002
其中，参考文献
[1]A CFD ANALYSIS TOWARDS FLOW CHARACTERISTICS OF THREE PRE-SWIRL DESIGNS Adrien Dulac Master of Science Thesis Royal Institute of Technology,Sweden
[2]扩口孔型预旋喷嘴流动与温降特性 刘高文等 推进技术 2013.4 34卷第3期
[3]叶型孔式预旋喷嘴流动叶型数值研究 刘育心等 推进技术 2016.2 37卷第2期
[4]长径比对预旋孔流动特性影响的数值研究 刘高文等 推进技术 2013.5 34卷第5期
本发明虽然以较佳实施例公开如上，但其并不是用来限定本发明，任何本领域技术人员在不脱离本发明的精神和范围内，都可以做出可能的变动和修改。因此，凡是未脱离本发明技术方案的内容，依据本发明的技术实质对以上实施例所作的任何修改、等同变化及修饰，均落入本发明权利要求所界定的保护范围之内。

Claims (7)

  1. 用于燃气涡轮的叶型管式喷嘴，其特征在于，包括顺着气流流动方向依次相接的入口段、收缩段和出口段，所述入口段为一段环形通道，所述收缩段包括由多个叶片分隔开的多个气流流通通道，每个所述气流流通通道由外周壁面、内周壁面、两相邻叶片之一的吸力面以及所述两相邻叶片另一个的压力面围成，该气流流通通道的入口呈扇形截面；顺着气流流动方向看，对于每个所述气流流通通道，从该气流流通通道的入口到出口，扇形截面逐步光滑过渡为圆形截面，其中所述两相邻叶片设置成主导气流在该喷嘴的圆周方向的转折，而所述外周壁面、所述内周壁面设置成主导气流在该喷嘴的半径方向的转折；所述出口段包括对应各个该气流流通通道的出口分别连接的、直径不沿轴线变化的圆形管道。
  2. 如权利要求1所述的叶型管式喷嘴，其特征在于，所述出口段为以螺旋线为轴线的螺旋管，所述螺旋线过所述圆形截面的圆心，所述螺旋线在所述圆形截面圆心处的切线与所述圆形截面的法向量平行。
  3. 如权利要求1所述的叶型管式喷嘴，其特征在于，所述圆形截面的圆心与所述圆形管道的出口之间的沿所述圆形管道的轴线的轴向距离，为所述圆形管道的轴向长度，处在0.1～5倍于所述圆形截面的直径之间。
  4. 如权利要求1所述的叶型管式喷嘴，其特征在于，所述出口段为以直线为轴线的直管，所述轴线通过所述圆形截面的圆形，并平行于所述圆形截面的法向量。
  5. 如权利要求1所述的叶型管式喷嘴，其特征在于，所述入口段为一段环形通道。
  6. 如权利要求1所述的叶型管式喷嘴，其特征在于，所述圆形管道以一直线的投影线为轴线，所述投影线为所述直线在所述圆形管道的起始圆形截面圆心所在的回转面上的投影，所述回转面是以所述起始圆形截面的圆心至该叶型管式喷嘴的轴心的垂线为直径且沿平行于该叶型管式喷嘴的轴向拉伸的圆柱面。
  7. 如权利要求1所述的叶型管式喷嘴，其特征在于，所述叶型管式喷嘴用于航空发动机高压涡轮中的预旋冷却系统，将冷气折转后再送入高压涡轮转子叶根。
PCT/CN2017/094921 2017-04-26 2017-07-28 用于燃气涡轮的叶型管式喷嘴 Ceased WO2018196198A1 (zh)

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CA3062856A CA3062856C (en) 2017-04-26 2017-07-28 Blade profile tube nozzle for gas turbine
EP17907287.1A EP3617480B1 (en) 2017-04-26 2017-07-28 Impeller tube-type nozzle for gas turbine
KR1020197033529A KR102364454B1 (ko) 2017-04-26 2017-07-28 가스 터빈용 임펠러형 튜브타입 노즐
JP2020509137A JP2020518764A (ja) 2017-04-26 2017-07-28 ガスタービン用ブレード付きのダクト型ノズル
US16/609,044 US11028708B2 (en) 2017-04-26 2017-07-28 Blade profile tube nozzle for gas turbine
RU2019136870A RU2729589C1 (ru) 2017-04-26 2017-07-28 Сопло с трубкой лопаточного профиля для газовой турбины

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CA3062856C (en) 2022-07-19
EP3617480B1 (en) 2022-12-14
EP3617480A1 (en) 2020-03-04
US20200149424A1 (en) 2020-05-14
KR20190138854A (ko) 2019-12-16
US11028708B2 (en) 2021-06-08
JP2020518764A (ja) 2020-06-25
CN108798790B (zh) 2019-09-17
EP3617480A4 (en) 2021-01-06

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