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Publication numberUS3867066 A
Publication typeGrant
Publication dateFeb 18, 1975
Filing dateAug 1, 1973
Priority dateMar 17, 1972
Publication numberUS 3867066 A, US 3867066A, US-A-3867066, US3867066 A, US3867066A
InventorsFred Canova, Leroy M Krouse, Hanns Hornschuch
Original AssigneeIngersoll Rand Co
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Gas compressor
US 3867066 A
Abstract
The arrangement is described in use in a gas compressor which is of the axial flow type, having a plurality of stages of compression, and an overhung rotor. The arrangement comprises vane mounting rings, for emplacement within a cylindrical housing, in which the stator vanes are pinned. Further, each vane is set in an elastomer for dampening or to accommodate for vibratory movement thereof. A housing and frame enclose and support the working elements of the compressor, the elements being so supported and enclosed as to allow for relative movements of the housing without causing distortion of said elements.
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Description  (OCR text may contain errors)

United States Patent [191 Canova et al.

[4 1 Feb. 18, 1975 GAS COMPRESSOR [75] Inventors: Fred Canova, Phillipsburg; Leroy M. Krouse; Hanns Hornschuch, both of [21] Appl. No.: 384,450

Related US. Application Data [62] Division of Ser. No. 235,501, March 17, 1972, Pat.

2,773,365 12/1956 Delf et al. 416/134 FOREIGN PATENTS OR APPLICATIONS 713,187 11/1941 Germany 416/134 248,891 3/1970 U.S.S.R 415/217 148,304 9/1952 Australia 415/217 Primary Examiner-Henry F. Raduazo Attorney, Agent, or FirmBernardl J. Murphy [5 7] ABSTRACT The arrangement is described in use in a gas compressor which is of the axial flow type, having a plurality of stages of compression, and an overhung rotor. The arrangement comprises vane mounting rings, for emplacement within a cylindrical housing, in which the stator vanes are pinned. Further, each vane is set in an elastomer for dampening or to accommodate for vibratory movement thereof. A housing and frame enclose and support the working elements of the compressor, the elements being so supported and enclosed as to allow for relative movements of the housing without causing distortion of said elements.

3 Claims, 4 Drawing Figures GAS COMPRESSOR This is a divisiori of application Ser. No. 235,501; filed Mar. 17, 1972 now US. Pat. No. 3,773,430.

This invention pertains to stator vane mounting arrangements for use in gas compressors, and in particular to gas compressors of the axial flow type where stator vanes are subject to vibration-induced failures a plurality of stages of compression.

It is an object of this invention to set forth a stator vane mounting arrangement which especially accommodates for vibratory movement of stator vanes. Especially it is an object of this invention to teach means for dampening vibratory movement of stator vanes.

Another object of this invention is to set forth an arrangement for mounting stator vanes in a stator housing, for use in a gas compressor, comprising a vane mounting ring, said ring having a recess formed therein for receiving a vane therewithin; a vane having an end thereof disposed within said recess; pin means securing said vane end in said recess; and resilient means enveloping said vane end and dampening said vane against vibration.

Further objects and features of this invention will be come more apparent by reference to the following description taken in conjunction with the accompanying figures, in which:

FIG. I is an axial view, partly in cross-section, of an arrangement for mounting stator vanes in use in a embodiment of a gas compressor, according to the invention;

FIG. 2 is an enlarged view of a detailed area of FIG. I; and

FIGS. 3 and 4 are side and plan views depicting the stator vane and mounting ring arrangements.

As shown in the figures, the novel gas compressor comprises a housing 12 having a base 14 for supporting the housing thereupon. A pair of oppositely disposed gas inlet flanges 16 are mounted to each side of the housing, the flanges defining inlet ports 18 which open on a chamber 20 defined within the housing At the axial outlet end of the compressor is mounted a gas discharge flange 22 having an outlet port 24 formed therein.

Upstream of the inlet end are carried coupling means and a bearing housing assembly (not shown), the two being supported in a casing 26 which is fixed to the compressor base 14. An over-hung, axially extending rotor and shaft assembly 28 is rotatably supported at but one axial end in the bearing housing, for rotary, gas-compressing movement within a compression chamber 30, and includes pluralities of radially disposed blades 32. A vaned stator 34, concentrically disposed about the rotor and shaft assembly, is mountedly supported within the compressor housing, by means of a cylindrical housing 36 which carries vane mounting rings 38 therewithin. The stator 34 comprises a plurality of such vane mounting rings in juxtaposition, each of which has fixed therein a plurality of vanes 40. All of the vanes 40 are of uniform length; however, the sta tor mounting rings 38 are of uniformly varying crosssection, from the inlet end to the outlet end of the compression chamber so that, toward the outlet end, progressively less of the vanes 40 protrudes into the compression chamber 30. Each vane 40 is pinned into its respective mounting ring 38 and, further, each vane head 42 is set in an elastomer 44 for the purpose of damping vane vibration.

The housing base 14 comprises a vertical plate 46 which has passageways (not shown) formed therein for the admittance of ambient atmosphere as a sealant and also for introducing lubricating oil. Also, the lubricating oil is conducted by drilled passageway 48 from an nular seals 50,50aset about the shaft of the rotor and shaft assembly 28 and subsequently drains into the bearing housing assembly.

The rotor and shaft assembly 28 comprises a plurality ofjuxtapositioned blade mounting rings 52, each of the rings having a plurality of the blades 32 mounted therein and radially extending away therefrom. Each blade 32 at the head end thereof has a forked extension 54 which is bored through to receive a pin 56. Further, each blade mounting ring has a plurality of boreholes 58 formed therethrough for retaining opposite ends of the blade-retaining pins. Each blade, at the head end thereof, has a laterally extending tang 60 which protrudes into a complementary, interfacing recess 62 provided therefor in an adjacent blade head end. Finally, the forked extensions 54 of adjacent blades have cooperative, arcuate cut-outs 64 formed therein with an elastomeric insert 66 therebetween. The pinning of the forked extensions, and the elastomeric inserts, cooperate to allow the blades to swing through a small arc to accommodate for vibration.

The rotor shaft has a hollow extension 68 about which the rotor blade mounting rings 52 are mounted.

At the outlet end of the gas compressor is disposed a diffuser shell 72 which is open at both, opposite, ends. One end is in direct open communication with the outlet end of the compression chamber 30, and the end opposite opens directly onto the outlet port 24. One end, the outlet end of this diffuser shell, is retained by a circumferential shoulder 74 formed within the outlet flange and about the outlet port. The diffuser shell outlet end and the circumferential shoulder have a compliant, sealant medium 76 therebetween. Further, the compressor housing has a radially and inwardly extending weldment 78 which abuttingly receives a radial ring 80 formed about and extending from the diffuser shell, said weldment and ring having an O-ring seal 82 therebetween.

Another ring 82 is welded within the outlet end of the housing, intermediate the weldment 78 and the outlet end of the diffuser shell 72, to present a flat-surfaced annulus for slidably supporting the diffuser shell therewithin. Four ribs 86 (only one is shown), equally spaced therebetween about the rotor axis, are fixed at either ends thereof to the annulus of ring 84 and the weldment 78 to provide further support for the diffuser shell therewithin and for the outlet end of the compressor.

The blade mounting rings 52 of the rotor, and the vane mounting rings 38 of the stator as well, are each independently replaceable. The innermost blade mounting ring (i.e., the one nearest the inlet end of the compression chamber) is set up against a circumferential shoulder 88 formed in the outer surface of the rotor shaft extension 68. Successive adjacently-disposed blade mounting rings 52 are set against the innermost one, along the shaft axis. The last or outermost blade mounting ring is secured on the rotor shaft extension by a retainer plate 90 bolted (by means not shown) to the shaft extension.

The vane mounting rings 38 of the stator, similarly are set one against the one adjacent thereto, with the innermost one set against a radial shoulder 92 formed in a cylindrical stator housing 36. The outermost vane mounting ring is secured in position by means of a bistepped retainer ring 96. One step 98 of the retainer ring abuttingly receives the outlet end of the stator housing 94, and the retainer ring is secured to said stator housing thereat. The other step 100 of the retainer ring, being disposed on a face of the ring opposite the first-mentioned step, abuttingly receives the inlet end of the diffuser shell 72. O-ring seals are disposed in both steps to fluid seal the joints formed thereat with the abutting components.

The novel stator vane mounting arrangement herein described in conncation with a compressor, due to the independent replaceability of the vane mounting rings 38, renders maintenance and repair easy, and accommodates a facile re-rating of the compressor. Simply by replacing given outermost mounting rings with dummy rings or spacers, or by wholly substituting differentlydimnsioned and/or configured vanes in replacement mounting rings, the performance of the compressor can be altered.

While we have described our invention in connection with a specific embodiment thereof, it is to be clearly understood that this is done only by way of example and not as a limitation to the scope of our invention as set forth in the objects thereof and in the appended claims.

We claim:

1. An arrangement for mounting stator vanes in a stator housing, for use in a gas compressor, comprising:

a vane mounting ring, said ring having a recess formed therein for receiving a vane therewithin;

a vane having an end thereof disposed within said recess, with a pin therethrough securing said vane end to said ring and in said recess; and

resilient means enveloping said vane end in said recess and dampening said vane against vibration.

2. An arrangement, according to claim 1, wherein: said resilient means comprises an elastomer.

3. An arrangement, according to claim 2, wherein: said elastomer wholly envelops said vane end and fills "M050 UNI'IED STATES PATEIIi OFFICE (5/69) CERT FlCFiTE 6F CQHRECTEQII Patent No. 3 r 867 I 066 Dated Inventor(s) Fred Canova, et al.

It is certified that error appears in the. above-identified patent and that said Letters Patent are hereby corrected as shown below:

On the first page of the patent, the INID Code [75] information should read: --Fred Canova, Phillipsburg, N..J. Leroy M. Krouse, Hanns Hornschuch, and-Paul Herman, Easton, PA; Joseph A. Dopkin, Hopewell, N.J.

Signed and sealed this 13th day of May 1975..

(SEAL) Attest:

C. MARSHALL DANN RUTH C. MASON Commissioner of Patents Attesting- Officer and Trademarks

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US2290607 *Mar 13, 1939Jul 21, 1942De Lavaud Robert SensaudPropeller
US2773365 *Nov 23, 1953Dec 11, 1956Delf George AVibration-damping hub and shaft assemblies
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US4293053 *Dec 18, 1979Oct 6, 1981United Technologies CorporationSound absorbing structure
US4940386 *Feb 4, 1988Jul 10, 1990Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A."Multiple flow turbojet engine with an outer ring of the fan outlet shrunk onto the case
US5073084 *Sep 17, 1990Dec 17, 1991Rolls-Royce PlcSingle-price labyrinth seal structure
US5074752 *Aug 6, 1990Dec 24, 1991General Electric CompanyGas turbine outlet guide vane mounting assembly
US5163817 *May 3, 1991Nov 17, 1992United Technologies CorporationRotor blade retention
US5429479 *Feb 24, 1994Jul 4, 1995Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma"Stage of vanes free at one extremity
US5690469 *Jun 6, 1996Nov 25, 1997United Technologies CorporationMethod and apparatus for replacing a vane assembly in a turbine engine
US6102664 *Dec 14, 1995Aug 15, 2000The United States Of America As Represented By The Administrator Of The National Aeronautics And Space AdministrationBlading system and method for controlling structural vibrations
US6409472Jul 31, 2000Jun 25, 2002United Technologies CorporationStator assembly for a rotary machine and clip member for a stator assembly
US6543995 *Jul 31, 2000Apr 8, 2003United Technologies CorporationStator vane and stator assembly for a rotary machine
US6619917 *Dec 19, 2000Sep 16, 2003United Technologies CorporationMachined fan exit guide vane attachment pockets for use in a gas turbine
US6984108Feb 24, 2003Jan 10, 2006Drs Power Technology Inc.Compressor stator vane
US7651319Apr 18, 2005Jan 26, 2010Drs Power Technology Inc.Compressor stator vane
US7984548Oct 31, 2007Jul 26, 2011Drs Power Technology Inc.Method for modifying a compressor stator vane
US20030231957 *Feb 24, 2003Dec 18, 2003Power Technology IncorporatedCompressor stator vane
US20050191177 *Apr 18, 2005Sep 1, 2005Anderson Rodger O.Compressor stator vane
US20080282541 *Oct 31, 2007Nov 20, 2008Anderson Rodger OCompressor stator vane
US20090110552 *Oct 31, 2007Apr 30, 2009Anderson Rodger OCompressor stator vane repair with pin
EP0017306A1 *Jan 24, 1980Oct 15, 1980Rolls-Royce LimitedStator vane assembly for a gas turbine engine
EP1079075A2 *Aug 9, 2000Feb 28, 2001United Technologies CorporationStator assembly for a rotary machine and clip member for a stator assembly
EP1079075A3 *Aug 9, 2000Aug 1, 2001United Technologies CorporationStator assembly for a rotary machine and clip member for a stator assembly
EP1741878A2 *Jun 30, 2006Jan 10, 2007Rolls-Royce plcFluid flow machine
EP1741878A3 *Jun 30, 2006Jun 4, 2008Rolls-Royce plcFluid flow machine
EP1762703A2Sep 12, 2006Mar 14, 2007Pratt & Whitney Canada Corp.Foreign object damage resistant vane assembly
EP1762703A3 *Sep 12, 2006Jan 20, 2010Pratt & Whitney Canada Corp.Foreign object damage resistant vane assembly
Classifications
U.S. Classification415/209.3, 416/500
International ClassificationF01D5/16, F04D29/66, F01D9/04, F01D5/30, F04D19/02, F04D29/32
Cooperative ClassificationF01D5/16, F04D19/02, F01D5/30, F01D9/042, F04D29/668, Y10S416/50, F04D29/322
European ClassificationF04D29/66C8, F01D9/04C, F04D29/32B2, F04D19/02, F01D5/30, F01D5/16