Source: http://www.google.com/patents/US7204675?ie=ISO-8859-1
Timestamp: 2015-05-07 10:31:12
Document Index: 205010028

Matched Legal Cases: ['art 21', 'art 21', 'art 21', 'art 21', 'art 21', 'art 22', 'art 21', 'art 22']

Patent US7204675 - Cooled gas turbine engine vane - Google PatentsSearch Images Maps Play YouTube News Gmail Drive More »Sign inAdvanced Patent SearchPatentsA cooled gas turbine vane includes a cast part and a longitudinal sleeve obtained by shaping metal sheet The cast part includes a longitudinal body provided with a longitudinal cavity having a first opening and a second opening at the ends The sleeve is mounted in the cavity by being firmly affixed to...http://www.google.com/patents/US7204675?utm_source=gb-gplus-sharePatent US7204675 - Cooled gas turbine engine vaneAdvanced Patent SearchPublication numberUS7204675 B2Publication typeGrantApplication numberUS 10/916,435Publication dateApr 17, 2007Filing dateAug 12, 2004Priority dateAug 12, 2003Fee statusPaidAlso published asCA2478954A1, CA2478954C, EP1508670A2, EP1508670A3, US20050089395Publication number10916435, 916435, US 7204675 B2, US 7204675B2, US-B2-7204675, US7204675 B2, US7204675B2InventorsChristophe TexierOriginal AssigneeSnecma MoteursExport CitationBiBTeX, EndNote, RefManPatent Citations (16), Referenced by (3), Classifications (15), Legal Events (5) External Links: USPTO, USPTO Assignment, EspacenetCooled gas turbine engine vane
US 7204675 B2Abstract
A cooled gas turbine vane includes a cast part and a longitudinal sleeve obtained by shaping metal sheet The cast part includes a longitudinal body provided with a longitudinal cavity having a first opening and a second opening at the ends The sleeve is mounted in the cavity by being firmly affixed to the wall of the first opening, and one end part of which being free to slide in the second opening forming a guide. The end part includes a part having constricted dimensions relative to the transverse dimensions of the guide.
1. A cooled gas turbine engine vane comprising a cast part and a longitudinal sleeve, for guiding the flow of cooling air, obtained by shaping sheet metal, the cast part comprising a longitudinal body provided with a longitudinal cavity having a first opening for feeding and a second opening for evacuation of air at the extremities, the sleeve being mounted in the cavity, by being attached to the wall of the first opening, one end part of which being free to slide into the second opening forming a guide, wherein said end part guided by the guide comprises a constriction of its passage crossing-section for the air flow, wherein a dimension of said constriction diminishes while extending away from the cavity.
2. The vane according to claim 1, wherein the sleeve is attached to the wall of the first opening by welding or by brazing.
3. The vane according to claim 1, wherein the constriction is obtained by folding the end of the sleeve.
4. The vane according to claim 3, wherein the folding is of curved profile section.
5. The vane according to claim 1, wherein the sleeve is perforated.
6. The vane according to claim 5, wherein the cast part comprises calibrated perforations.
7. A cooled gas turbine engine vane comprising:
a cast part comprising a longitudinal body defining a longitudinal cavity with a first opening and a second opening;
a longitudinal sleeve made of sheet metal and configured to guide a flow of cooling air, said sleeve being mounted in said cavity and attached to a wall of the first opening, and said sleeve having an end part that is free to slide into the second opening; and
means for forming an air flow constriction at said end part of said sleeve and for reducing static pressure at an outlet of said sleeve,
wherein said means have a dimension that diminishes away from the cavity.
8. The vane according to claim 7, wherein said means comprise a folded portion of said end part of the sleeve.
9. The vane according to claim 7, wherein said means comprise a perforated plate.
10. The vane according to claim 7, wherein the sleeve is perforated.
11. The vane according to claim 7, wherein the cast part comprises calibrated perforations.
12. A cooled gas turbine engine vane comprising:
a longitudinal sleeve made of sheet metal and configured to guide a flow of cooling air, said sleeve being mounted in said cavity and attached to a wall of the first opening, and said sleeve having an end part that is free to slide into the second opening:
means for forming an air flow constriction at said end part of said sleeve and for reducing static pressure at an outlet of said sleeve; and
wherein said means comprise a tube having a conical shape and cross-section dimensions that diminish away from the cavity.
13. A cooled gas turbine engine vane comprising:
a tube attached to said end part of the sleeve and forming an air flow constriction, wherein the tube has a conical shape, whose cross-section dimensions diminish while extending from the end part of the sleeve.
The present invention relates to the cooling of vanes in a gas turbine engine, in particular the vanes of a turbine nozzle.
In a gas turbine engine, the air is compressed in a compressor and is mixed with a fuel in the combustion chamber. The flow leaving the latter feeds one or several turbines stages, before being ejected into an exhaust nozzle.
The turbine stages comprise rotors separated by nozzles, or distributors, for orienting the gas flow. Because of the temperature of the gas that passes over them, the vanes are subjected to very severe operating conditions; it is therefore necessary to cool them, generally by forced convection or even by air impact on the inside of the vanes.
FIG. 1 represents a distributor vane 1 of the prior art, wherein the cooling is assured by a multi-perforated longitudinal sleeve 4. The vane 1 extends between two platforms: an inner platform 3 and an outer platform 2, which delimits the annular gas circulation channel 5 within the turbine. This channel is subdivided circumferentially by the vanes 1.
The multi-perforated sleeve 4 is slid longitudinally into the central cavity 6 of the vane 1. At the level of the outer platform 2, a duct 7 feeds the sleeve 4 with cold air taken from the compressor, for example. Because of the pressure difference existing between the inside of the sleeve 4 and the peripheral zone of the cavity 6 delimited by the outside wall of the sleeve 4 and the inside wall of the vane 1, a portion of the air is projected via the perforations of the sleeve 4 against the inside wall of the vane 1, thus assuring its cooling. This air is then evacuated in the gas stream 5, along the trailing edge of the vane 1, by calibrated perforations. The rest of the air is evacuated across the inner platform 3 into a second duct 8, which guides it towards the other parts of the motor to be cooled, such as the turbine disk or the turbine bearings.
The central cavity 6 of the vane 1 comprises two openings 9, 10 at the level of the outer platform 2 and the inner platform 3, respectively. At the time of assembly of the vane, the sleeve 4 is slid through the outer opening 9 of the vane 1 and firmly affixed to the outer platform 2, generally by brazing along the wall of the outer opening 9. The opposing part of the sleeve 4 is guided into the inner opening 10 of the vane 1, forming a guide into the inner platform 3 in order to authorize relative displacements between the sleeve and the vane. (This is why the inner opening 10 is also referred herein to as the guide 10.) Indeed, because of the differences between the materials and the manufacturing methods between the vane 1 and the sleeve 4, as well as between the operating temperatures, there results a variation in elongation between the vane 1 and the sleeve 4. The guide 10 helps maintain the configuration of the vane assembly.
The vane 1 is formed by casting, while the sleeve 4 is formed by shaping of a metal sheet. Considering the difference between the methods of manufacturing the vane 1 and the sleeve 4, the clearance along the guide 10 is relatively significant; this clearance results especially from the manufacturing tolerances. It creates an air leak at the level of the exit from the sleeve 4, since the pressure in the peripheral zone of the cavity 6 is lower than that in the central canal formed by the sleeve 4.
Referring to FIG. 2, the air leak represented by the arrow F has the first drawback of creating an overpressure in the peripheral zone of the cavity 6. This overpressure is prejudicial to the internal cooling of the vane 1, and more particularly at the level of the leading edge zone, which is the hottest zone, since the air passing in the central cavity of the sleeve 4 has less tendency to be projected via the perforations of the sleeve 4 against the inside wall of the vane 1. Moreover, the air coming from the leakage does not participate in the cooling of the vane, since it is guided directly towards the evacuation orifices situated on the trailing edge. In addition, the quantity of air guided into the duct 8 in order to cool other parts of the engine is reduced by virtue of the leakage.
It has been proposed to eliminate the air leakage by means of sealing systems, but these latter adversely affect the sliding of the sleeve 4 in the guide 10, necessary to the compensation of the dilatation differences mentioned above.
The present invention proposes eliminating these drawbacks.
To this end, the invention relates to a cooled gas turbine engine vane comprising a cast part and a longitudinal sleeve for guiding the flow of cooling air obtained by shaping sheet metal, the cast part comprising a longitudinal body provided with a longitudinal cavity with a first opening for feeding and a second opening for evacuation of air at the extremities, the sleeve being mounted in the cavity by being attached to the wall of the first opening, one end part of which being free to slide into the second opening forming a guide, characterized in that said end portion guided by the guide comprises a constriction of its passage cross-section for the air flow.
The solution proposed by the invention is simple and economical. It also offers the advantage of making it possible to calibrate the cooling flow of the disks.
The invention will be better appreciated in virtue of the following description of the vane according to the invention, with reference to the appended drawings, wherein:
FIG. 1 represents a sectional profile view of a prior art vane;
FIG. 2 represents a sectional profile view of the sleeve in the guide of the vane of FIG. 1;
FIG. 3 represents a sectional profile view of a first embodiment of the vane according to the invention;
FIG. 4 represents a sectional profile view of the sleeve in the guide of the vane of FIG. 3;
FIG. 5 represents a sectional profile view of the sleeve of a second embodiment of the vane according to the invention, and
FIG. 6 represents a sectional profile view of the sleeve of a third embodiment of the vane according to the invention.
Although the invention applies to any type of vane, it will be described especially in connection with a turbine nozzle vane.
With reference to FIG. 3, the distributor vane 11 according to the invention extends between an outer platform 12 and an inner platform 13 of the gas turbine engine nozzle, which delimits an annular gas circulation channel 15 in the turbine. It comprises a central longitudinal cavity 16 having two openings, an outer 19 and an inner 20, at the level of the outer platform 12 and the inner platform 13, respectively.
A sleeve 14 is inserted into the central cavity 16 of the vane, accommodating a peripheral cooling cavity between the outside wall of the sleeve 14 and the inside wall of the vane 11. The sleeve 14 is attached to the wall of the outer opening 19 of the vane 11 by brazing or welding, for example. In addition, it is guided at an end part 21 into the inner opening 20 forming a sliding guide for this purpose. Accordingly, it is possible for it to slide into the guide 20 in order to make the assembly of the vane united, notwithstanding the differential dilatations between its various elements.
At the outer platform 12, the sleeve 14 is supplied by a duct 17 with air coming from the cooler levels of the turbine engine. Because of the pressure difference existing between the central cavity of the sleeve 14 and the peripheral cooling cavity of the cavity 16, a portion of this air is projected from the central cavity of the sleeve 14 towards the inside wall of the vane by perforations provided to this end on the sleeve 14, especially on the side of the leading edge of the vane 11. This air is then evacuated by calibrated perforation on the trailing edge of the vane 11.
The portion of the air not projected onto the inner wall of the vane 11 is evacuated from the sleeve 14 through a duct 18 extending at the level of the inner platform 13 following the guide 20.
With reference to FIG. 4, the sleeve 14 of the vane 11 of FIG. 3, formed by folding sheet metal, is folded in the zone of its end portion 21 guided by the guide 20 so as to form a constriction 22 for the air flow that is guided into its cavity. More precisely, the constriction 22 is realized in the zone of the end part 21 of the sleeve 14 arranged to be located inside the guide 20. In the embodiment of FIG. 4, this folding has a curved profile.
In fact, the objective is to create, in the end part 21 of the sleeve 14 guided by the guide 20, a zone 22, the transverse dimensions of which are clearly constricted relative to the transverse dimensions of the guide 20.
Accordingly, in virtue of the folding of the sleeve 14, a loss of load is created at the folded end 22 of the sleeve 14. This loss of load causes a drop in the static pressure at the outlet of the sleeve 14. Consequently, in virtue of an ad hoc conformation of the fold, it is possible to regulate the static pressure at the outlet of the sleeve 14 relative to the static pressure of the cooling zone of the cavity 16 of the vane in such a fashion as to eliminate, or at least reduce, within the guide 20, the leakage of air at the outlet of the sleeve 14 towards said cooling zone.
Accordingly, in virtue of the invention, it is possible to remedy the air leakage without changing the structure nor the mode of realizing the body of the vane 11, by suitably conforming the end part 21 of the sleeve 14, without additional production costs.
FIG. 5 represents a second embodiment of a sleeve 14′ of the vane 1. In the latter, it is proposed, in order to obtain results identical to the previous ones, brazing or welding, to the end of the end part 21′ of the sleeve 14′ intended to be guided by the guide 20, a calibrated plate 23′ perforated over the greater part of its surface, in the present case, of an air passage opening 24′. In this fashion, a part 22′ having constricted transverse dimensions relative to the transverse dimensions of the guide 20 is obtained.
FIG. 6 represents a third embodiment of a sleeve 14″ of the vane 1. In this latter instance, it is proposed to braze a conical tube 23″, whose transverse dimensions narrow in moving away from the sleeve end 14″, to the end of the end part 21″ of the sleeve 14′ intended to be guided by the guide 20. In this fashion, a part 22″ having constricted transverse dimensions relative to the transverse dimensions of the guide 20 is obtained.
The third embodiment of the sleeve according to the invention is advantageous relative to the second in that it makes it possible to minimize the load losses at the inlet of the cone.
Patent CitationsCited PatentFiling datePublication dateApplicantTitleUS3767322Jul 30, 1971Oct 23, 1973Westinghouse Electric CorpInternal cooling for turbine vanesUS4288201 *Sep 14, 1979Sep 8, 1981United Technologies CorporationVane cooling structureUS4962640 *Feb 6, 1989Oct 16, 1990Westinghouse Electric Corp.Apparatus and method for cooling a gas turbine vaneUS5511937Sep 30, 1994Apr 30, 1996Westinghouse Electric CorporationGas turbine airfoil with a cooling air regulating sealUS5749701 *Oct 28, 1996May 12, 1998General Electric CompanyInterstage seal assembly for a turbineUS6065928 *Jul 22, 1998May 23, 2000General Electric CompanyTurbine nozzle having purge air circuitUS6109867Nov 25, 1998Aug 29, 2000Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A."Cooled turbine-nozzle vaneUS6561757 *Aug 3, 2001May 13, 2003General Electric CompanyTurbine vane segment and impingement insert configuration for fail-safe impingement insert retentionUS7008185 *Feb 27, 2003Mar 7, 2006General Electric CompanyGas turbine engine turbine nozzle bifurcated impingement baffleUS20030026689Aug 3, 2001Feb 6, 2003Burdgick Steven SebastianTurbine vane segment and impingement insert configuration for fail-safe impingement insert retentionEP0381955A1Jan 17, 1990Aug 16, 1990Westinghouse Electric CorporationGas turbine with air-cooled vanesEP0974733A2Jul 14, 1999Jan 26, 2000General Electric CompanyTurbine nozzle having purge air circuitEP1149982A2Dec 8, 2000Oct 31, 2001General Electric CompanyA method of joining a vane cavity insert to a nozzle segment of a gas turbineEP1154124A1May 4, 2001Nov 14, 2001General Electric CompanyImpingement cooled airfoilEP1191189A1Sep 26, 2000Mar 27, 2002Siemens AktiengesellschaftGas turbine bladesEP1251243A1Apr 17, 2002Oct 23, 2002Snecma MoteursTurbine blade with cooling air baffle* Cited by examinerReferenced byCiting PatentFiling datePublication dateApplicantTitleUS7921654Sep 7, 2007Apr 12, 2011Florida Turbine Technologies, Inc.Cooled turbine stator vaneUS8353668Feb 18, 2009Jan 15, 2013United Technologies CorporationAirfoil insert having a tab extending away from the body defining a portion of outlet peripheryUS20120224975 *May 16, 2012Sep 6, 2012SnecmaProcess for the vapor phase aluminization of a turbomachine metal part and donor liner and turbomachine vane comprising such a liner* Cited by examinerClassifications U.S. Classification416/96.00A, 415/115, 415/191International ClassificationF01D9/02, F01D5/18, F02C7/18Cooperative ClassificationF05D2250/323, F05D2250/141, F05D2250/232, F05D2250/292, F05D2260/201, F05D2250/70, F05D2250/71, F01D5/188European ClassificationF01D5/18G2Legal EventsDateCodeEventDescriptionSep 29, 2014FPAYFee paymentYear of fee payment: 8Sep 28, 2010FPAYFee paymentYear of fee payment: 4Feb 20, 2008ASAssignmentOwner name: SNECMA, FRANCEFree format text: CHANGE OF NAME;ASSIGNOR:SNECMA MOTEURS;REEL/FRAME:020609/0569Effective date: 20050512Owner name: SNECMA,FRANCEFree format text: CHANGE OF NAME;ASSIGNOR:SNECMA MOTEURS;US-ASSIGNMENT DATABASE UPDATED:20100330;REEL/FRAME:20609/569Free format text: CHANGE OF NAME;ASSIGNOR:SNECMA MOTEURS;US-ASSIGNMENT DATABASE UPDATED:20100427;REEL/FRAME:20609/569Free format text: CHANGE OF NAME;ASSIGNOR:SNECMA MOTEURS;REEL/FRAME:20609/569Owner name: SNECMA,FRANCEFree format text: CHANGE OF NAME;ASSIGNOR:SNECMA MOTEURS;US-ASSIGNMENT DATABASE UPDATED:20100427;REEL/FRAME:20609/569Effective date: 20050512Owner name: SNECMA,FRANCEFree format text: CHANGE OF NAME;ASSIGNOR:SNECMA MOTEURS;REEL/FRAME:020609/0569Effective date: 20050512Owner name: SNECMA,FRANCEFree format text: CHANGE OF NAME;ASSIGNOR:SNECMA MOTEURS;REEL/FRAME:20609/569Effective date: 20050512Owner name: SNECMA,FRANCEFree format text: CHANGE OF NAME;ASSIGNOR:SNECMA MOTEURS;US-ASSIGNMENT DATABASE UPDATED:20100330;REEL/FRAME:20609/569Effective date: 20050512Aug 28, 2007CCCertificate of correctionDec 17, 2004ASAssignmentOwner name: SNECMA MOTEURS, FRANCEFree format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:TEXIER, CHRISTOPHE;REEL/FRAME:016086/0655Effective date: 20040712RotateOriginal ImageGoogle Home - Sitemap - USPTO Bulk Downloads - Privacy Policy - Terms of Service - About Google Patents - Send FeedbackData provided by IFI CLAIMS Patent Services