WO1996028642A1 - Wear resistant gas turbine engine airseal assembly - Google Patents
Wear resistant gas turbine engine airseal assembly Download PDFInfo
- Publication number
- WO1996028642A1 WO1996028642A1 PCT/US1996/003410 US9603410W WO9628642A1 WO 1996028642 A1 WO1996028642 A1 WO 1996028642A1 US 9603410 W US9603410 W US 9603410W WO 9628642 A1 WO9628642 A1 WO 9628642A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- rail
- airseal
- contact surface
- ring rail
- ring
- Prior art date
Links
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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
-
- 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
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
-
- 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
- F05D2230/60—Assembly methods
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
- F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
-
- 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
- F05D2230/90—Coating; Surface treatment
Definitions
- the present invention relates to gas turbine engines and, more particularly, to airseal assemblies therefor.
- Conventional gas turbine engines include a compressor, a combustor, and a turbine.
- the sections of the gas turbine engine are sequentially situated about a longitudinal axis and enclosed in an engine case. Air flows axially through the engine.
- Air flows axially through the engine.
- air compressed in the compressor is mixed with fuel, ignited and burned in the combustor.
- the hot products of combustion emerging from the combustor are expanded in the turbine, thereby rotating the turbine and driving the compressor.
- Both the compressor and the turbine include alternating rows of rotating airfoils and stationary airfoils, also commonly referred to as blades and vanes, respectively.
- Each airfoil includes an airfoil portion flanged by an outer diameter portion and an inner diameter portion.
- the blades are secured within a rotating disk.
- the vanes are typically cantilevered from the engine case.
- the outer diameter portion of each vane is mounted on the engine case at a forward attachment point and a rear attachment point.
- the airseal prevents higher pressure air from leaking to a lower pressure area.
- the airseals currently used in gas turbine engines are a one piece design, fabricated from a metal alloy.
- the existing airseal includes an annular airseal body with an integrally machined forward and rear rails spaced apart from each other and extending radially outward from the airseal body.
- a flange disposed on the inner diameter portion of the vane fits into the space between the forward and the rear rails.
- the rear rail is shorter than the forward rail.
- the coating is a high durability, high temperature, wear resistant metal that must be sprayed onto the surface in a flame spray or plasma spray operation.
- For the coating to be sprayed onto the surface there must be access to the surface, also referred to as a "line of sight".
- the contact surface of the forward rail of the existing airseal is accessible for the application of the coating, because the rear rail is shorter than the forward rail.
- the rear rail is not accessible for spraying with a layer of wear resistant coating because the longer forward rail blocks the line of sight thereto. Therefore, the rear rail of the present design remains unprotected.
- the rate of wear is greater on the rear rail than on the forward rail because the rear rail is shorter than the forward rail. It is well known in the art that the rate of wear is a function of the contact area.
- the rear rail having a smaller area of contact with the vane flange, wears faster than the forward rail. Extensive wear of the rear rail results in leaning of the vane toward the row of the rotating blades. If the rear rail is completely worn through, the vane will clash with the row of turbine blades adjacent to the row of vanes. Such contact between the vane and the rotating blades is detrimental to engine performance and potentially may result in engine failure.
- Another approach for reducing wear of the rear rail is to increase the area of contact between the vane and the rear rail.
- a longer rear rail would make current assembly procedure impossible and would also block the line of sight for spraying the forward rail with wear resistant coating, thereby preventing coating of the forward rail.
- Another option for reducing rear rail wear is to fabricate the entire airseal from a more wear resistant metal.
- One such metal could be cobalt.
- manufacturing the entire airseal from cobalt or a similar wear resistant metal would be extremely expensive and, therefore cost prohibitive.
- an airseal assembly for a gas turbine engine includes an annular first airseal having an airseal body with a forward rail extending radially outward therefrom and a ring rail attaching onto the first airseal and being spaced apart from the forward rail by a plurality of spacers to fit a vane flange of a gas turbine engine vane between the forward rail and the ring rail.
- the present invention allows the forward rail and the ring rail to be sprayed with wear resistant coating individually prior to assembly. The wear resistant coating protects the forward rail and the ring rail from wear induced by the relative motion between the rails and the vane flange, and thus prolongs the service life thereof.
- the contact surface of the ring rail that comes in contact with the vane flange is partially tapered toward the radially outer end of the ring rail. It is well known in the art that the increased area of contact between the metal parts reduces the rate of wear thereof.
- the tapered surface increases the area of contact between the vane flange and the ring rail as the initial contact surface of the ring rail begins to wear. Thus, the tapered surface of the present invention slows the rate of wear as the wear progresses.
- One primary advantage of the present invention is that the ring rail can be fabricated such that it is radially longer.
- the extra length of the ring rail will increase the contact area between the ring rail and the vane flange when inevitable wear will occur, thereby, reducing the rate of wear of the ring rail.
- the extended length of the ring rail will not prevent spraying of the forward rail with the wear resistant coating, because the forward rail can be sprayed with the wear resistant coating prior to assembly. Furthermore, the assembly process will not be hindered by the extended length of the ring rail because the tapered surface provides sufficient clearance for the vanes to be fitted between the forward and rear rails.
- the ring rail can be fabricated from cobalt or from other similar wear resistant materials.
- the relatively small size of the ring rail makes it economically feasible to manufacture the ring rail from much more expensive metals than the conventional materials that are used to fabricate airseals.
- Another advantage of the present invention is that once the ring rail eventually becomes worn, only the ring rail has to be replaced, rather than the entire airseal. This advantage represents significant cost savings during operational life of the airseal because the loading on the ring rail is greater than on the forward rail, thereby requiring more frequent repair or replacement of the ring rail than of the forward rail.
- FIG. 1 is a simplified, partially broken away representation of a gas turbine engine
- FIG. 2 is an enlarged, simplified, fragmentary representation of a vane mounted onto a gas turbine engine case and having an airseal assembly fitted thereon, according to the present invention
- FIG. 3 is a cross-sectional elevation of the airseal assembly of FIG. 2;
- FIG. 4 is an exploded, perspective elevation of the airseal assembly of FIG. 3 with vane clusters fitting therein;
- FIG. 5 is a partially broken away, side elevation of the airseal assembly of FIG. 4 with vane clusters fitted therein;
- FIG. 6 is an enlarged, partially broken away elevation of the airseal assembly of FIG. 5 with a ring rail having a tapered surface, according to the present invention;
- FIG. 7 is a partially broken away elevation of the airseal assembly of FIG. 6 that has been worn; and FIG. 8 is a cross-sectional elevation of an alternate embodiment of the airseal assembly. Best Mode for Carrying out the Invention
- a gas turbine engine 10 includes a compressor 12, a combustor 14, and a turbine 16. Sections 12, 14, 16 of the gas turbine engine 10 are sequentially situated about a longitudinal axis 18 and are enclosed in an engine case 20. Air 22 flows axially through the sections 12, 14, 16 of the engine 10.
- the compressor 12 and the turbine 16 include alternating rows of rotating blades 24 and stationary vanes 26. The rotating blades 24 are secured onto a rotating disk 28.
- the stationary vanes 26 are cantilevered from the engine case 20.
- the vane 26 comprises an airfoil portion 30 flanged by an outer diameter buttress 32 and an inner diameter buttress 34.
- the outer diameter buttress 32 includes a forward hook 36 and a rear hook 38.
- the forward hook 36 and the rear hook 38 are secured within the engine case 20 at a forward attachment point 40 and a rear attachment point 42, respectively.
- the inner diameter buttress 34 has a vane flange 46 protruding therefrom.
- the flange 46 includes a slot 48.
- FIGs. 4 and 5 depict vanes 26 arranged in vane clusters 50 of three vanes 26 per each cluster 50.
- Each vane cluster 50 shares one inner diameter buttress 34 and one outer diameter buttress 32.
- the vane flange 46 of the inner diameter buttress 34 fits into an airseal assembly 54.
- the airseal assembly 54 includes a first annular airseal 56, a ring rail 58, and a plurality of spacers 60.
- the first airseal 56 has an airseal body 62 with an upstream end 64 and a downstream end 66 and a forward rail 68 extending radially outward from the upstream end 64 of the airseal body 62.
- the forward rail 68 includes a forward rail contact surface 70 that comes into contact with the vane flange 46.
- the forward rail 68 has a plurality of forward rail openings 72 formed therein.
- the ring rail 58 has an inner diameter end 74, an outer diameter end 76, and a ring rail contact surface 80 therebetween.
- the ring rail contact surface 80 comes into contact with the vane flange 46 and faces the forward rail contact surface 70.
- the ring rail 58 includes a plurality of ring rail openings 82 spaced to be in register with the forward rail openings 72.
- Each spacer 60 is sized to fit into the slot 48 of the vane cluster 50.
- Each spacer 60 has a spacer opening 84 formed therein.
- the forward rail contact surface 70 and the ring rail contact surface 80 are sprayed with wear resistant coating.
- the ring rail openings 82 are lined up to be in register with the forward rail openings 72 so that the ring rail 58 is spaced apart from the forward rail 68 by the plurality of spacers 60.
- the assembly is then fastened together by means of either a bolt 86, or a pin or some other fastening device with the fastening device 86 passing through the ring rail opening 82, the spacer opening 84, and the forward rail opening 72.
- the vane flanges 46 of the vane clusters 50 are fitted into the airseal assembly 54 with the spacers 60 fitting into the slots 48, as best shown in FIG. 5.
- the spacers 60 function as anti-rotational devices that prevent the airseal assembly 54 from rotating.
- the airseal and the vane subassembly is then placed into the engine case 20 with the forward hook 36 and the rear hook 38 of each vane 26 fitting into the engine case 20 at the forward attachment point 40 and the rear attachment point 42, as shown in FIG. 2.
- the present invention significantly reduces the wear of the rear rail 58 of the airseal assembly 54.
- the wear resistant coating applied on the ring rail contact surface 80 retards the wear of the ring rail 58, thereby prolonging the service life of the airseal assembly 54 substantially.
- FIG. 6 illustrates another feature of the present invention.
- the ring rail 58 includes a tapered surface 88 that intersects with the ring rail contact surface 80 and extends tapering off toward the outer diameter end 76 of the ring rail 58.
- the tapered surface 88 slows down the rate of the wear of the ring rail 58.
- the initial ring rail contact surface 80 has a predetermined radial length 90, as shown in FIG. 6.
- the wear resistant coating significantly reduces the rate of wear, the initial ring rail contact surface 80 will inevitably wear.
- the radial length 190 of the subsequent contact surface 180 of the ring rail increases as a result of the tapered surface 88, as shown in FIG. 7.
- the increase in the subsequent contact surface 180 reduces the rate of wear of the ring rail 58.
- the airseal assembly 54 of the present invention is more wear resistant because the ring rail contact surface 80 is accessible for spraying with coating and because the tapered surface 88 increases the subsequent contact area between the vane flange 46 and the ring rail 58.
- the present invention permits an even greater area of contact between the vane flange 46 and the ring rail contact surface 80 by increasing the radial length of the ring rail 58 without adverse consequences.
- the tapered surface 88 provides sufficient clearance for the vane flange 46 to be fitted between the forward rail 68 and the ring rail 58 so that the assembly process remains unaffected.
- the additional length of the ring rail 58 does not effect the accessibility of the forward rail 68 for wear resistant coating spray because the forward rail 68 is sprayed prior to assembly.
- the present invention makes it economically feasible to fabricate the ring rail 58 from a more expensive and more wear resistant material such as cobalt. Since the ring rail 58 is relatively small compared to the entire airseal assembly 54, it is not financially prohibitive to manufacture only a small part of the airseal assembly from cobalt or similar material having wear resistant properties.
- an alternate embodiment of an airseal assembly 254 includes a first airseal 256 having an airseal body 262 with a forward rail 268 extending radially outward therefrom and an L- shaped ring rail 258 attaching onto the airseal body 262.
- the ring rail 258 is attached to the airseal body 262 by means of either rivets 286, as shown in FIG. 8, or can be welded onto the airseal body 262.
- the plurality of spacers 260 are shown to be integral with the forward rail 268 of the first airseal 256. However, the spacers 260 can be also integral with the ring rail 258.
- the spacers 60 are depicted having square shape, spacers having any shape will fall within the scope of the present invention as long as the forward rail 68 and the ring rail 58 are spaced apart and the airseal assembly 54 is prevented from rotation.
- the novelty of the present invention lies in having the airseal segmented in at least two portions such that contact surfaces 70, 80 of each rail 68, 58 can be sprayed with wear resistant coating prior to assembly. Therefore, to practice the present invention, the airseal assembly can be segmented at any point as long as the forward and ring rails are disposed on separate segments so that the contact surfaces of each rail can be sprayed with wear resistant coating prior to assembly of the airseal.
- the airseal assembly depicted is for the second stage turbine vane, the invention is applicable for any stage of either compressor or turbine vane.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP52779996A JP3764168B2 (en) | 1995-03-15 | 1996-03-13 | Abrasion resistant air seal assembly for gas turbine engines |
DE69606392T DE69606392T2 (en) | 1995-03-15 | 1996-03-13 | Abrasion-proof storage of a sealing ring in a gas turbine |
EP96909676A EP0815353B1 (en) | 1995-03-15 | 1996-03-13 | Wear resistant gas turbine engine airseal assembly |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US40422495A | 1995-03-15 | 1995-03-15 | |
US404,224 | 1995-03-15 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO1996028642A1 true WO1996028642A1 (en) | 1996-09-19 |
Family
ID=23598693
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/US1996/003410 WO1996028642A1 (en) | 1995-03-15 | 1996-03-13 | Wear resistant gas turbine engine airseal assembly |
Country Status (4)
Country | Link |
---|---|
EP (1) | EP0815353B1 (en) |
JP (1) | JP3764168B2 (en) |
DE (1) | DE69606392T2 (en) |
WO (1) | WO1996028642A1 (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1148209A3 (en) * | 2000-04-19 | 2003-05-07 | Rolls-Royce Deutschland Ltd & Co KG | Interstage seal configuration |
FR2984428A1 (en) * | 2011-12-19 | 2013-06-21 | Snecma | COMPRESSOR RECTIFIER FOR TURBOMACHINE. |
FR3003894A1 (en) * | 2013-03-29 | 2014-10-03 | Snecma | ROTATING LOCKING MEMBER FOR A DISTRIBUTOR AND A RING OF A TURBOMACHINE |
EP2971615A4 (en) * | 2013-03-15 | 2017-01-11 | United Technologies Corporation | Low leakage duct segment using expansion joint assembly |
WO2020135709A1 (en) * | 2018-12-29 | 2020-07-02 | Nissens Automotive A/S | A nozzle ring structure |
US11499437B2 (en) | 2020-03-06 | 2022-11-15 | MTU Aero Engines AG | Sealing apparatus for a turbomachine, seal-carrier ring element for a sealing apparatus, and turbomachine |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP4822716B2 (en) * | 2005-02-07 | 2011-11-24 | 三菱重工業株式会社 | Gas turbine with seal structure |
US8684683B2 (en) * | 2010-11-30 | 2014-04-01 | General Electric Company | Gas turbine nozzle attachment scheme and removal/installation method |
JP5134703B2 (en) * | 2011-04-27 | 2013-01-30 | 三菱重工業株式会社 | Gas turbine with seal structure |
Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE721066C (en) * | 1940-04-02 | 1942-05-23 | Siemens Ag | Disc exposed to lateral overpressure, in particular radially loaded blade or labyrinth carrier, for centrifugal machines, preferably steam or gas turbines |
US2488867A (en) * | 1946-10-02 | 1949-11-22 | Rolls Royce | Nozzle-guide-vane assembly for gas turbine engines |
US3066911A (en) * | 1959-05-12 | 1962-12-04 | Thompson Ramo Wooldridge Inc | Nozzle and turbine wheel shroud support |
FR2086275A1 (en) * | 1970-04-23 | 1971-12-31 | Westinghouse Electric Corp | |
GB2069064A (en) * | 1980-01-31 | 1981-08-19 | Mtu Muenchen Gmbh | Turbomachine stator vane mounting |
EP0320620A1 (en) * | 1987-11-19 | 1989-06-21 | Abb Stal Ab | Gas turbine with a sealing ring movably connected to a guide vane ring |
EP0493111A1 (en) * | 1990-12-27 | 1992-07-01 | United Technologies Corporation | Gas turbine with modulation of cooling air |
DE4309200A1 (en) * | 1993-03-22 | 1994-09-29 | Abb Management Ag | Device for the suspension and removal of parts subject to high thermal loads in turbine plants |
-
1996
- 1996-03-13 EP EP96909676A patent/EP0815353B1/en not_active Expired - Lifetime
- 1996-03-13 JP JP52779996A patent/JP3764168B2/en not_active Expired - Fee Related
- 1996-03-13 WO PCT/US1996/003410 patent/WO1996028642A1/en active IP Right Grant
- 1996-03-13 DE DE69606392T patent/DE69606392T2/en not_active Expired - Lifetime
Patent Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE721066C (en) * | 1940-04-02 | 1942-05-23 | Siemens Ag | Disc exposed to lateral overpressure, in particular radially loaded blade or labyrinth carrier, for centrifugal machines, preferably steam or gas turbines |
US2488867A (en) * | 1946-10-02 | 1949-11-22 | Rolls Royce | Nozzle-guide-vane assembly for gas turbine engines |
US3066911A (en) * | 1959-05-12 | 1962-12-04 | Thompson Ramo Wooldridge Inc | Nozzle and turbine wheel shroud support |
FR2086275A1 (en) * | 1970-04-23 | 1971-12-31 | Westinghouse Electric Corp | |
GB2069064A (en) * | 1980-01-31 | 1981-08-19 | Mtu Muenchen Gmbh | Turbomachine stator vane mounting |
EP0320620A1 (en) * | 1987-11-19 | 1989-06-21 | Abb Stal Ab | Gas turbine with a sealing ring movably connected to a guide vane ring |
EP0493111A1 (en) * | 1990-12-27 | 1992-07-01 | United Technologies Corporation | Gas turbine with modulation of cooling air |
DE4309200A1 (en) * | 1993-03-22 | 1994-09-29 | Abb Management Ag | Device for the suspension and removal of parts subject to high thermal loads in turbine plants |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1148209A3 (en) * | 2000-04-19 | 2003-05-07 | Rolls-Royce Deutschland Ltd & Co KG | Interstage seal configuration |
FR2984428A1 (en) * | 2011-12-19 | 2013-06-21 | Snecma | COMPRESSOR RECTIFIER FOR TURBOMACHINE. |
WO2013093337A1 (en) * | 2011-12-19 | 2013-06-27 | Snecma | Turbomachine compressor guide vanes assembly |
CN104011333A (en) * | 2011-12-19 | 2014-08-27 | 斯奈克玛 | Turbomachine compressor guide vanes assembly |
US9702259B2 (en) | 2011-12-19 | 2017-07-11 | Snecma | Turbomachine compressor guide vanes assembly |
EP2971615A4 (en) * | 2013-03-15 | 2017-01-11 | United Technologies Corporation | Low leakage duct segment using expansion joint assembly |
US10451204B2 (en) | 2013-03-15 | 2019-10-22 | United Technologies Corporation | Low leakage duct segment using expansion joint assembly |
FR3003894A1 (en) * | 2013-03-29 | 2014-10-03 | Snecma | ROTATING LOCKING MEMBER FOR A DISTRIBUTOR AND A RING OF A TURBOMACHINE |
WO2020135709A1 (en) * | 2018-12-29 | 2020-07-02 | Nissens Automotive A/S | A nozzle ring structure |
US11499437B2 (en) | 2020-03-06 | 2022-11-15 | MTU Aero Engines AG | Sealing apparatus for a turbomachine, seal-carrier ring element for a sealing apparatus, and turbomachine |
Also Published As
Publication number | Publication date |
---|---|
JPH11502006A (en) | 1999-02-16 |
EP0815353B1 (en) | 2000-01-26 |
EP0815353A1 (en) | 1998-01-07 |
DE69606392T2 (en) | 2000-09-07 |
DE69606392D1 (en) | 2000-03-02 |
JP3764168B2 (en) | 2006-04-05 |
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