US3525574A - Vane ring for turbo-engines - Google Patents

Vane ring for turbo-engines Download PDF

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Publication number
US3525574A
US3525574A US779357A US3525574DA US3525574A US 3525574 A US3525574 A US 3525574A US 779357 A US779357 A US 779357A US 3525574D A US3525574D A US 3525574DA US 3525574 A US3525574 A US 3525574A
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US
United States
Prior art keywords
blade
axle
housings
journal
bearing
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.)
Expired - Lifetime
Application number
US779357A
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English (en)
Inventor
Ferdinand Zerlauth
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Sulzer AG
Original Assignee
Sulzer AG
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 Sulzer AG filed Critical Sulzer AG
Application granted granted Critical
Publication of US3525574A publication Critical patent/US3525574A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • 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
    • 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

  • This invention relates to a vane ring for turboengines. More particularly, this invention relates toa coolant system for a vane ring for turbo-engines.
  • Vane rings for turbo-engines have been known to carry a plurality of angularly adjustable blades so as to adapt to changes in load conditions. Because of the mountings which have been used in securing these blades in place, it has in some cases been difficult to obtain a sufficient cooling of the blade mountings in a simple manner.
  • the invention provides a cooling system for a vane ring for turbo-engines wherein blades are journalled in axle housings outside of a blade carrier supporting the blades.
  • the cooling system is constructed to deliver a coolant to at least the bearing zones of each axle housing in order to cool the bearings as well as the axle housings.
  • the axle housings are arranged in groups with each housing in a group having connection apertures for the introduction of coolant into suitable spaces within the housing about the bearing zones.
  • Each connection aperture is situated perpendicularly to the vane ring plane in mutually facing relation to the connection aperture of an adjoining housing.
  • an expansion pipe is disposed between each pair of adjoining housings to interconnect the opposed connection apertures of the housings so that coolant can pass between the housings.
  • at least one of the axle housings is provided with a port for introduction of a coolant, such as a cooling gas, from an outside source.
  • the expansion pipes in one embodiment are provided at their extremities with joining rings or flanges to facilitate connection to the respective axle housings. Also, the length of an expansion pipe in a relaxed state is preferably greater than the distance between the two mutually facing connection apertures so that the expansion pipe is preloaded upon insertion between the connection apertures. As a result of the preload, the expansion pipes are tightly connected to the axle housings about the connection apertures in sealed relation.
  • the expansion pipes are formed by bellowstype hoses whose junction points are additionally pressed against the connection apertures beyond the preload as a result of their internal pressure.
  • connection apertures of adjoining axle c ICC housings can alternatively be arranged in planes inclined with respect to the housing axis in such a way that the mutually facing apertures of adjoining housings are parallel with respect to one another and that, as a result, the expansion pipe axis remains straight.
  • FIG. 1 illustrates a fragmentary cross-sectional view of a vane ring incorporating a cooling system according to the invention taken on line II of FIGS. 2 to 4;
  • FIG. 2 illustrates a view taken on line IIII of FIG. 1;
  • FIG. 3 illustrates a view taken in the plane of line IIIIII of FIG. 1 of two adjacent axle housings
  • FIG. 4 illustrates a view taken on line IV-IV of FIG. 1;
  • FIG. 5 illustrates a cross-sectional view of a modified blade design and coolant passageway according to the ininvention
  • FIG. 6 illustrates a modified connection between adjacent bearing axle housings for the coolant flow.
  • the vane ring includes an annular blade carrier 1 and a plurality of blades, for example, twenty-eight, which are circumferentially spaced and carried on the blade carrier 1 substantially radially of the rotor shaft (not shown) in the ring plane IIIIII.
  • the blade carrier 1 is formed with a bore 2 for each blade as well as with a recess 3 about the bore 2 for receiving an axle housing 4 of a bearing mount.
  • Each blade is formed with a part 5 which contacts the working medium, a neck 6 substantially within the plane of the blade carrier 1, a blade journal 7 and an axle journal 8 secured about the blade journal 7.
  • the part 5 merges into the neck 6 at the lower end while the neck 6 which is provided with cooling ribs 23 merges into the blade journal 7 to form a one-piece blade.
  • This blade is further either forced into the journal 8 or is shrunk on by undercooling.
  • the blade and journal 8 can be made as a compound cast element, for example, by precision cast ing and by forming part 5 of a heat resistant steel and by forming the other parts, particularly at the bearing surfaces, of a material having suitable dry operation properties.
  • Each axle housing 4 is individually secured to the blade carrier 1 and is formed with an inner wall 9 of tubular shape which carries a pair of bearings 10, 11 in supporting relation to the axle journal 8.
  • the axle housing 4 is also formed with an outer wall 20 by which the axle housing 4 is supported in the recess 3.
  • the outer wall 20 also supports the inner wall 9 at two spaced points via annular supports 12, 13 while forming an open hollow space 14 and a closed hollow space 15 between the walls 9, 20.
  • the open hollow space 14 is situated at a point closer to the blade carrier 1 than the closed hollow space 15 while being in facing relation to the blade carrier 1.
  • the closed hollow spaces 15 of at least one group of axle housings 4 are interconnected by means of connection apertures 48 in opposite surfaces of the outer wall 20 and expansion pipes 17 and together constitute a distribution line 16 which supplies each one of the connected axle housings 4 of the group with a partial amount of a gaseous coolant, for instance, air.
  • at least one of the axle housings 4 of a group is further connected via a port 51 in the outer wall 20 with a supply line 19 (FIG. 2) which provides the total amount of gas required for the cooling of all the housings 4 of the group connected to the distribution line 16.
  • two supply pipes can be attached to the lower half of the blade carrier and connected to the two axle housings 4 next to their respective axial separating 3 planes. Following joining of the lower and upper half of the blade carrier and installation of the connecting pipes 17, an inherently closed distribution line 16 is produced with two substantially diametrically opposite supply connections. During inspection. and cleaning operations of the vane rings, the supply lines need not be removed.
  • each expansion pipe 17 is provided with annular rings at the ends which serve to mount the pipe 17 on the axle housings 4 coaxially of the connection apertures 48.
  • Each annular ring is secured to a axle housing, for example, by means of bolts (not shown).
  • the expansion pipes 17 can be of a length that is greater than the spacing between adjoining axle housings 4. That is, the expansion pipes 17 can be installed between the axle housings 4 by means of a suitable tool and then expanded against the housings 4. The expansion tubes 17 are thus urged elastically against the apertures 48 of the axle housings 4 and are also pressed against the apertures 48 in a preloaded state as a result of internal pressure.
  • connecting rings 49 are connected to the ends of the expansion pipes 17 and are preferably provided with collars 50 to form gripping surfaces.
  • the connecting rings 49 can be seated in recesses about the connection apertures 48 as shown.
  • the connection apertures can be disposed in planes inclined to the axle housing axes so that the opposed apertures of adjacent housings are parallel to each other. This allows the expansion pipes to remain straight instead of being slightly curved to the radius of the vane ring.
  • the open hollow space 14 and the closed hollow space 15 which forms a part of the distribution conduit 16 in each housing are interconnected by means of bores 18. These bores 18 allow the partial amount of the cooling gas required for each axle housing 4 to be branched off from the distribution line 16 to the individual cooling sites.
  • a displacement body 39 of U-shaped cross-section and discontinuous length is mounted in the open space 14 in inverted manner to form a pair of narrow coolant flow passages with the walls 9, 20.
  • the outer leg of the body 39 is of greater length than the inner and rests on a plate 22 in the recess 3 of the blade carrier 1. Bores 38 are provided in the lower end of this outer leg to permit coolant fio'w towards the blade neck 6.
  • bearings 10, 11 aflixed at both ends of the cylindrical bore formed by the inner wall 9, such are formed of a plastic capable of withstanding dry operation free of lubricants as well as elevated temperatures, for example, a plastic known as DU. Such plastics are able to withstand temperatures up to 200 C. and above without sulfering any damage, and exhibit slide properties which do not make it necessary to provide for a special supply of lubricants.
  • the axle journal 8 designed for these bearings is of a material capable of sliding without wear and without a special supply of lubricant on the bearing plastic selected without either impairing itself or the bearings 10, 11.
  • Each axle housing 4 includes a peripheral flange 21 near the base of the outer wall 20 which facilitates tightening of the housing 4 against the blade carrier 1 and the plate 22 positioned therebetween.
  • the flange 21 surrounds the axle housing 4 at a distance from the blade carrier 1 so as to minimize the transmission of heat from the blade carrier 1 to the axle housing 4.
  • the opposite end of the axle housing 4 has a thrust bearing mounted between the axle journal 8 and the housing 4.
  • the thrust bearing includes a rotor disk 24 secured to the journal 8, a pair of sliding disks 25 on opposite sides of the rotor disk 24, and a mounting plate 26 secured on the housing 4 over the disks 24, 25.
  • a sealing ring 55 is further mounted in a groove of the disk 26 to prevent an escape of cooling gas out of the axle housing 4 along the journal 8 into the space surrounding the blade carrier 1.
  • a hub 27 of an adjustable lever 28 is keyed over the end of the journal 8 to sealingly engage the sealing ring and to clamp the rotor disk 24 and the sliding disks 25 together against a shoulder 29 of the axle journal 8 so that the disks 24, 25 follow the rotational motions of the journal 8 and lever 28'.
  • the cooling ribs 23 on the neck 6 of the blade are surrounded by a sleeve 30 mounted with a slight clearance within the plate 22.
  • the sleeve 30 is compressed at one end by means of the spring 31 against a recess 32 of a ring segment 33 of the blade carrier 1 and is prevented from falling out of the plate 22 by means of a circlip 34 in a groove at the other end.
  • the sleeve 30 is fitted tightly onto the cooling ribs 23 so as to be centered by the blade free of resistance in the plate 22.
  • a plurality of bores 39 are provided in the sleeve 30 to cornmunicate the opposite sides of the sleeve with each other.
  • the cooling ribs 23 are provided with milled sections 35 alternating from rib to rib by a semi-circumference and thereby face each other in two groups.
  • cooling air is supplied over the supply line 19 (FIG. 1), for instance at a temperature of approximately C., and distributed into hollow space 15. Portions of the cooling air are then passed through each of the connection apertures 48 and bores 18 in the housing 4. The portions of cooling air passing through the connection apertures 48 flow through the expansion pipes 17 connected to the sides of the housing 4 (FIG. 3) into the adjoining axle housings 4 of the housing group for subsequent passage and distribution in the other housings of the group.
  • the air separates again into two halves and flows in this manner between the second and third ribs of the blade neck. After leaving the intermediary space bordering the last rib, the air passes on through the bores 39 of the sleeve 30 into the space surrounding these bores and flows then through ducts (not shown) into the flow passage of the work medium within the blade carrier 1.
  • the bearing points of the blades in particular the bearing 10 situated closest to the blade carrier 1 and, hence, to the flow of the work medium, can be kept at a temperature capable of insuring trouble-free operation.
  • the cooling gas also acts simultaneously as a blocking gas for the axle housing 4 in view of the fact that its pressure must always be greater than the pressure of the working medium in the rotor space. This prevents the penetrating of working medium or residues thereof into the axle housing 4 and, as a result of impurities or foreign substance that are carried along, in particular upon running in of the engine, the soiling of the bearing surfaces of the axle journal 8.
  • the seal 55 because of the seal 55, the space between the inner wall 9 and the axle journal 8 is sealed off with respect to the space surrounding the blade carrier 1 so that even in the case of a possible overpressure of the working medium, the
  • the part 5 contacted by the working medium can have a temperature up to 600 C. and more.
  • a flow of heat can be produced over the blade neck 6, the blade journal 7, the axle journal 8, and the bearings 10, 11 against areas of a lower temperature at the outside of the engine.
  • this heat flow is substantially reduced ahead of the bearing as a considerable amount of heat is drawn off by the cooling air at the cooling ribs 23 before the heat reaches the blade journal 8.
  • An additional heat transmission loss of the heat flow can be achieved by reducing the cross-section of the blade journal 8 and blade neck 6 by means of a central bore 40 in the blade and, as a result, the conduction cross-section of the heat flow.
  • the bearing sleeve 10 is cooled from the outside by means of the cooling air passing along at the free end of the inner wall 9.
  • the part of the cooling air passing along the inner side of the outer wall reduces the influx of heat from the blade carrier 1 through the outer wall 20 onto the supports 12, 13 of the inner wall 9 and hence to the bearing sleeves 10, 11.
  • a metallurgical connection is produced between the blade part 5 contacted by the work medium and the axle journal 8 in the area of the blade neck 6, for instance at the point 41 as shown.
  • an alloy is produced along a short stretch of the two different parts so that, after completion of the cast element, the blade appears as a single workpiece that can be machined.
  • the compound casting is arranged in such a way that the alloy site is at a point at which at least the work medium cannot supply any additional heat to the blade and, conversely, at which the blade is not yet fitted in a bearing.
  • the axle journal 8 is reduced in diameter at the point 42 and a bearing tube 43 is slid over the reduced portion and welded to the axle journal 8 to form a hollow space 44 and receive the bearing sleeve 10.
  • This hollow space 44 is connected by bores 45 in the journal 8 to the space 46 surrounding the blade neck 6 and, in addition, by means of radial bores 47 in the journal 8 with a central bore 40 in the journal 8.
  • the central bore 40 leads into the open so that a partial amount of the flow of coolant determined by a dosing bore is diverted in the space 46 and guided through the hollow space 44. As a result, the bearing tube 43 and the plastic bearing 10 fitted thereon are efficiently cooled.
  • a cooling system including an expansion pipe between each pair of adjacent axle housings of a group of said axle housings for conducting a flow of coolant therebetween, each said adjacent housing having a connection aperture therein in communication with said expansion pipe, said connection aperture being perpendicular to the plane of said vane ring.
  • each expansion pipe includes a connecting ring at each end secured to said axle housing thereat coaxially of said connection aperture thereat.
  • each expansion pipe includes a connecting ring at each end having a collar thereon.
  • each expansion pipe is a bellows-type hose and is preloaded between said adjacent axle housings.
  • connection apertures of said adjacent axle housings are in parallel planes and said expansion pipe is straight.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Mounting Of Bearings Or Others (AREA)
US779357A 1968-07-26 1968-11-27 Vane ring for turbo-engines Expired - Lifetime US3525574A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH1127868A CH494340A (de) 1968-07-26 1968-07-26 Leitschaufelkranz für Turbomaschinen III

Publications (1)

Publication Number Publication Date
US3525574A true US3525574A (en) 1970-08-25

Family

ID=4371894

Family Applications (1)

Application Number Title Priority Date Filing Date
US779357A Expired - Lifetime US3525574A (en) 1968-07-26 1968-11-27 Vane ring for turbo-engines

Country Status (7)

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US (1) US3525574A (de)
BE (1) BE731930A (de)
CH (1) CH494340A (de)
DE (1) DE1751810B1 (de)
FR (1) FR2013756A1 (de)
GB (1) GB1271823A (de)
NL (1) NL6811396A (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3652177A (en) * 1969-05-23 1972-03-28 Mtu Muenchen Gmbh Installation for the support of pivotal guide blades
US3695777A (en) * 1969-05-23 1972-10-03 Motoren Turbinen Union Supporting device for pivotal guide blades in thermal turbo-machines
US4007998A (en) * 1975-08-22 1977-02-15 Carrier Corporation Blade assembly

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2651496A (en) * 1951-10-10 1953-09-08 Gen Electric Variable area nozzle for hightemperature turbines
GB783970A (en) * 1954-09-17 1957-10-02 Napier & Son Ltd Gaseous fluid turbines
US2859935A (en) * 1951-02-15 1958-11-11 Power Jets Res & Dev Ltd Cooling of turbines
US3295823A (en) * 1965-10-13 1967-01-03 Raymond G H Waugh Gas turbine cooling distribution system using the blade ring principle
US3367628A (en) * 1966-10-31 1968-02-06 United Aircraft Corp Movable vane unit

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB579161A (en) * 1942-11-06 1946-07-25 Joseph Stanley Hall Improvements relating to elastic fluid turbines
GB755527A (en) * 1953-10-15 1956-08-22 Power Jets Res & Dev Ltd Mounting of swivelling guide vane elements in axial flow elastic fluid turbines
DE1273928B (de) * 1962-02-23 1968-07-25 United Aircraft Corp Dichte Verbindung zweier relativ zueinander beweglicher Rohrstutzen an Behaeltern

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2859935A (en) * 1951-02-15 1958-11-11 Power Jets Res & Dev Ltd Cooling of turbines
US2651496A (en) * 1951-10-10 1953-09-08 Gen Electric Variable area nozzle for hightemperature turbines
GB783970A (en) * 1954-09-17 1957-10-02 Napier & Son Ltd Gaseous fluid turbines
US3295823A (en) * 1965-10-13 1967-01-03 Raymond G H Waugh Gas turbine cooling distribution system using the blade ring principle
US3367628A (en) * 1966-10-31 1968-02-06 United Aircraft Corp Movable vane unit

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3652177A (en) * 1969-05-23 1972-03-28 Mtu Muenchen Gmbh Installation for the support of pivotal guide blades
US3695777A (en) * 1969-05-23 1972-10-03 Motoren Turbinen Union Supporting device for pivotal guide blades in thermal turbo-machines
US4007998A (en) * 1975-08-22 1977-02-15 Carrier Corporation Blade assembly

Also Published As

Publication number Publication date
GB1271823A (en) 1972-04-26
CH494340A (de) 1970-07-31
NL6811396A (de) 1970-01-29
DE1751810B1 (de) 1971-06-09
BE731930A (de) 1969-10-23
FR2013756A1 (de) 1970-04-10

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