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Publication numberUS3887299 A
Publication typeGrant
Publication dateJun 3, 1975
Filing dateAug 28, 1973
Priority dateAug 28, 1973
Publication numberUS 3887299 A, US 3887299A, US-A-3887299, US3887299 A, US3887299A
InventorsProfant Daniel
Original AssigneeUs Air Force
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Non-abradable turbine seal
US 3887299 A
Abstract
A non-abradable turbine seal for use between the blade member and surrounding shroud of the turbine engine. The seal may take on a variety of configurations, any one of which constructed to allow deformation thereof by the blade member, either because of rotor growth or shroud eccentricities. The seals are made of oxidation resistant compressible or crushable materials in the form of thin metallic foil, pads, ceramic hollow spheres or thin walled tubing.
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Description  (OCR text may contain errors)

United States Patent 1 Profant NON-ABRADABLE TURBINE SEAL [75] Inventor: Daniel Proiant, Glastonbury, Conn.

[73] Assignee: The United States of America as represented by the Secretary of the Air Force, Washington, DC.

[22] Filed: Aug. 28, 1973 [21] Appl. No.: 392,381

[52] US. Cl 415/174; 415/214 [51] Int. Cl. F0ld 11/08 [58] Field of Search 415/113, 172 A, 173, 174,

[56] References Cited UNITED STATES PATENTS 2,447,957 8/1948 Moore 415/174 2,927,724 3/1960 Wardle 415/113 2,994,472 8/1961 Botje l 415/174 3,042,367 7/1962 Welsh.... 415/113 3,146,992 9/1964 Farrell 415/174 III/114711111111 1 June 3, 1975 3,291,382 12/1966 Blackhurst et a1 415/214 3,502,596 3/1970 Sowards 3,542,152 11/1970 Adamson....... i. 415/214 3,575,427 4/1971 Lapac 415/174 3,708,242 1/1973 Bruneau et al. 415/214 3,720,419 3/1973 Adellizzi 415/174 Primary Examiner-Henry F. Raduazo Attorney, Agent, or Firm-Jacob N. Erlich [57] ABSTRACT A non-abradable turbine seal for use between the blade member and surrounding shroud of the turbine engine. The seal may take on a variety of configurations, any one of which constructed to allow deformation thereof by the blade member, either because of rotor growth or shroud ecc entricities. The seals are made of oxidation resistant compressible or crushable materials in the form of thin metallic foil, pads, ceramic hollow spheres or thin walled tubing.

3 Claims, 5 Drawing Figures NON-ABRADABLE TURBINE SEAL BACKGROUND OF THE INVENTION This invention relates generally to seals to be used with turbine blades, and more particularly, to compressible or crushable seals which permit the deformation thereof by either rotor shroud eccentricities or rotor growth.

It is well known that the efficiency of the gas turbine engine is dependent in part upon the dimensional tolerances that are maintained during the production of the engine assembly. A particularly difficult dimensional tolerance to maintain is concerned with the peripheral seal between the free ends of the rotor blades and the surrounding casing. The use of abradable sealing materials as a lining for the casings is well known in the art. Such materials have been used to avoid damage due to the rubbing contact of the rotor blades with the compressor casing and further, to effect the necessary seal between the moving parts.

The problems encountered by the use of abradable turbine outer seals are numerous. For example, these seals have either oxidized and/or eroded in the severe turbine environment or conversely, the more dense materials that resist erosion are not sufficiently abradable and cause excessive blade wear. In addition, the relatively high processing temperature required to manufacture such abradable materials creates problems of distortion and dimensional inaccuracy in the seal struc ture. As a result of such high processing temperature requirements, the abradable seal material is difficult to repair or patch after assembly in an engine or in an engine component.

SUMMARY OF THE INVENTION The instant invention sets forth a plurality of seal structures which are compressible or crushable and thereby overcome the problems set forth hereinabove.

The seals set forth in this invention permit seal deformation by either the turbine shroud eccentricities or the rotor growth but yet avoid the erosion which has occurred in porous, metallic abradable seal material utilized in the past. These seals are capable of being inserted within the shroud or spacer which surrounds the the blade member ofa conventional turbine engine and may take on a variety of configurations. For example, they may be formed of foil and subsequently brazed or welded to the shroud in such a manner to permit lateral movement thereof or in another modification the foil may be crimped to minimize tensile stresses during deformation in the engine. Additionally, cooling openings may be inserted in the shroud. Furthermore, the seal may take on the form of hollow spheres or folded sections manufactured of compressible metal or ceramic felt. Also this filler material may be in the form of thin walled tubesjoined together and then brazed within the shroud.

It is therefore an object of this invention to provide a non-abradable. compressible or crushable seal which is capable of use between relatively moveable parts.

It is another object of this invention to provide nonabradable seal material which is strong and lightweight.

It is a further object of this invention to provide a seal material which is economical to produce and which utilizes conventional, currently available components that lend themselves to standard mass producing manufacturing techniques.

For a better understanding of the present invention together with other and further objects thereof reference is made to the following description taken in connection with the accompanying drawing and its scope will be pointed out in the appended claims.

DESCRIPTION OF THE DRAWINGS FIG. 1 is a side elevational view of one embodiment of the non-abradable turbine seal of this invention. shown partially in cross section;

FIG. 2 is a side elevational view of another embodiment of the non-abradable turbine seal of this invention, shown partly in cross section;

FIG. 3 is a side elevational view of a further embodiment of the non-abradable turbine seal of this inven tion, shown partly in cross section;

FIG. 4 is a side elevational view of still another embodiment of the non-abradable turbine seal of this invention, shown partly in cross section; and

FIG. 5 is a side elevational view of further embodiments of the non-abradable turbine seal of this invention, shown partly in cross section.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Reference is now made to FIGS. l-5 of the drawing which set forth the plurality of non-abradable turbine seals of the instant invention. The turbine seals will be represented by numerals 10, 20, 30, 40 and S0 in FIGS. 1-5 of the drawing, respectively, and like elements in each figure will be identified by like numerals.

Generally, a shroud or spacer l2 cooperates with and surrounds a blade member 14, one of which rotates with respect to the other in a conventional turbine arrangement. For example, blade member 14 can be attached to a rotating compressor wheel (not shown) or shroud 12 can be carried between and rotate with rotating compressor wheels (not shown) opposite a stationary blade member 14. Located within shroud 12 and opposite blade member 14 is the turbine seal 10, 20, 30, 40 or 50 of this invention.

Reference is now made to FIG. 1 of the drawing which sets forth a rectangular-shaped non-abradable compressible seal 10 made up of a foil material 16. This seal 10 forms a housing which is secured within shroud l2. Foil 16 is of nominal 5-10 mil thickness and manufactured of an oxidation resistant and easily deformable metal such as NiCrAlY, FeCrAlY, Hastelloy X. Within foil housing 16 is a foil strip 18 of similar material to foil 16 but of sine-wave configuration. The foil housing 16 as well as the sine-wave foil 18 are welded or brazed together at appropriate places 19. The configuration as shown in FIG. 1 permits the lateral movement of turbine seal 10 under the action of blade 14.

Reference is now made to FIG. 2 of the drawing. The turbine seal 20 set forth therein has an upper foil member 22 made of any suitable easily deformable material as set forth hereinabove fixedly secured to shroud 12 with a plurality of curved foil sections 18 located therebetween. A plurality of apertures 24 are located within shroud l2 and allow for the admittance of cooling air or other fluid during the operation of the turbine. It should also be pointed out that apertures 24 are capable of being used within any embodiment shown in FIGS. 1-5.

FIG. 3 sets forth a crushable turbine seal 30 having an outer structure 16 similar in nature to the outer structure 16 in FIG. 1. in the embodiment shown in FIG. 3. however the sine-wave foil strip 18 is replaced by a plurality of crushable metal or ceramic hollow spheres 32. This arrangement again allows for the deformation of seal 30 under the action of blade 14.

FIG. 4 sets forth turbine seal 40 which contains therein a straight piece of foil material 42 within an outer foil housing 16 and further contains therein compressible metal or ceramic felt or matte 44 of about l-l5% density.

FIG. illustrates a turbine seal 50 which takes the form of a plurality of thin walled tubular shaped elements 52. Elements 52 may be of a cylindrical shape 54, oval shape 56 or hollow elements of any other desired configuration 58. Any suitable deformable material as set forth hereinabove can be utilized in their manufacture.

The non-abradable seals 10, 20, 30, 40 and 50 of this invention are capable of being interchanged within shroud 12 depending upon the type of blade 14 or shroud 12 construction. With the non-abradable seals set forth hereinabove virtually all problems heretofore encountered with abradable seals have been eliminated.

ill

Although this invention has been described with reference to a variety of embodiments which will be understood to those skilled in the art, this invention is also capable of further embodiments within the spirit and scope of the appended claims.

I claim.

1. In a turbine engine comprising a rotating blade member and a surrounding fixed shroud wherein said improvement comprises a non-abradable seal having an outer housing located within and fixed to said shroud. said outer housing being made of an easily deformable foil material and a thin deformable foil material of sinewave configuration being located within said outer housing with the peaks and depressions of the sinewave being directed axially and facing the rotating blade member; thereby allowing for the lateral displacement of said seal under the action of said rotating blade member.

2. In a turbine engine as defined in claim 1 wherein said foil material is between 5-10 mils thick.

3. In a turbine engine as defined in claim 2 wherein said foil material is NiCrAlY.

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US2447957 *Dec 29, 1945Aug 24, 1948Moore CoSeal for fans
US2927724 *Oct 2, 1957Mar 8, 1960Avro Aircraft LtdFloating blade shrouds
US2994472 *Dec 29, 1958Aug 1, 1961Gen ElectricTip clearance control system for turbomachines
US3042367 *Jul 17, 1958Jul 3, 1962Gen Motors CorpFluid seal
US3146992 *Dec 10, 1962Sep 1, 1964Gen ElectricTurbine shroud support structure
US3291382 *Mar 26, 1965Dec 13, 1966Rolls RoyceBladed structure, for example, for a gas turbine engine compressor
US3502596 *Nov 16, 1965Mar 24, 1970Du PontCeramic structures
US3542152 *Apr 8, 1968Nov 24, 1970Gen ElectricSound suppression panel
US3575427 *Nov 3, 1969Apr 20, 1971United Aircraft CorpComposite abradable seal
US3708242 *Nov 30, 1970Jan 2, 1973SnecmaSupporting structure for the blades of turbomachines
US3720419 *Jan 21, 1971Mar 13, 1973Westinghouse Electric CorpFabricated labyrinth seal structure
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US3966356 *Sep 22, 1975Jun 29, 1976General Motors CorporationBlade tip seal mount
US4207024 *Aug 4, 1978Jun 10, 1980The United States Of America As Represented By The Administrator Of The National Aeronautics And Space AdministrationComposite seal for turbomachinery
US4285633 *Oct 26, 1979Aug 25, 1981The United States Of America As Represented By The Secretary Of The Air ForceBroad spectrum vibration damper assembly fixed stator vanes of axial flow compressor
US4295786 *Nov 20, 1979Oct 20, 1981The United States Of America As Represented By The Administrator Of The National Aeronautics And Space AdministrationComposite seal for turbomachinery
US4349313 *Dec 26, 1979Sep 14, 1982United Technologies CorporationAbradable rub strip
US4411594 *Jun 22, 1982Oct 25, 1983Rolls-Royce LimitedSupport member and a component supported thereby
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US4636976 *Sep 28, 1984Jan 13, 1987Data General CorporationBit shifting apparatus
US7291946 *Jan 27, 2003Nov 6, 2007United Technologies CorporationDamper for stator assembly
US8739547Jun 23, 2011Jun 3, 2014United Technologies CorporationGas turbine engine joint having a metallic member, a CMC member, and a ceramic key
US8790067Apr 27, 2011Jul 29, 2014United Technologies CorporationBlade clearance control using high-CTE and low-CTE ring members
US8864492Jun 23, 2011Oct 21, 2014United Technologies CorporationReverse flow combustor duct attachment
US8920116 *Oct 7, 2011Dec 30, 2014Siemens Energy, Inc.Wear prevention system for securing compressor airfoils within a turbine engine
US8920127Jul 18, 2011Dec 30, 2014United Technologies CorporationTurbine rotor non-metallic blade attachment
US8985938Dec 13, 2011Mar 24, 2015United Technologies CorporationFan blade tip clearance control via Z-bands
US20130089417 *Oct 7, 2011Apr 11, 2013David J. WiebeWear prevention system for securing compressor airfoils within a turbine engine
CN102042045BOct 9, 2010May 7, 2014通用电气公司Shroud assembly with discourager
EP0256790A2 *Aug 6, 1987Feb 24, 1988AlliedSignal Inc.Ceramic lined turbine shroud and method of its manufacture
EP2604804A2 *Dec 11, 2012Jun 19, 2013United Technologies CorporationFan blade tip clearance control
Classifications
U.S. Classification415/173.4
International ClassificationF01D11/08, F01D11/12
Cooperative ClassificationF01D11/12
European ClassificationF01D11/12