CA1187809A - Heat-exchanger integrated with the stator box of a gas turbine - Google Patents
Heat-exchanger integrated with the stator box of a gas turbineInfo
- Publication number
- CA1187809A CA1187809A CA000408572A CA408572A CA1187809A CA 1187809 A CA1187809 A CA 1187809A CA 000408572 A CA000408572 A CA 000408572A CA 408572 A CA408572 A CA 408572A CA 1187809 A CA1187809 A CA 1187809A
- Authority
- CA
- Canada
- Prior art keywords
- connection member
- intermediate connection
- gas turbine
- gas
- upstream end
- 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
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
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/10—Heating, e.g. warming-up before starting
-
- 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
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/20—Actively adjusting tip-clearance
- F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
-
- 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
- F01D25/14—Casings modified therefor
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Motor Or Generator Cooling System (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
ABSTRACT OF THE DISCLOSURE:
A gas turbine wherein an intermediate connection member of a generator for the gas relative to the power stage or transition piece acts as a heat-exchanger for the stator box of said power stage with which it is ther-mally in contact with its downstream end. The intermediate connection member is provided with an electric heating coil embedded in its external surface and an inner annular chamber within which cooling air is caused to flow along a helical path from the downstream end to the upstream end of said chamber.
A gas turbine wherein an intermediate connection member of a generator for the gas relative to the power stage or transition piece acts as a heat-exchanger for the stator box of said power stage with which it is ther-mally in contact with its downstream end. The intermediate connection member is provided with an electric heating coil embedded in its external surface and an inner annular chamber within which cooling air is caused to flow along a helical path from the downstream end to the upstream end of said chamber.
Description
~713~
The present invention relates to a gas turbine having a heat-exchanger connected to its stator box.
In particular, the present invention relates to a heat-exchanger which is integrated with the stator box of a gas turbine, which, by permitting adequately to preheat said stator box prior to starting the turbine and then to cool it efficiently, makes also possible drastically to reduce the problems connected with the transient states of the gas ~urbine and thus to obtain high efficiencies in said turbines with lower costs and simpler constructional arrangements.
As is known, in a gas turbine and more particu larly in the power stage of a gas turbine high temperatures are experienced which originate considerable thermal expan-sions in the component parts concerned. However, while the rotorr Eor its having the vanes directly acted upon by the hot gases, expands immediately as the turbine is started, the stator box since its thickness is considerable, its position more external and subJected to more intense cooling, takes a longer time to become heated and thus to expand.
Thus, in order to prevent that during said tran-sient states the rotor portions, when expanded, may scrape the fixed stator portions with the possible atte:dan~
~'' /_._.
damages of the vanes andlor the sealing members, -the clearances between the ro-tor and the stator in the present gas turbines are held sufficiently wide and the result is a decrease of the efficiency of the tur-bine concerned.
The principal obJect of the present invention is thus to offset said defect and thus to provide a turbine having a high efficiency inasmuch as it becomes possible to keep narrow clearances between the rotor and -the sta-tor in the power stage.
Thls obJect is substantially achieved by virtueof the fact that the s-tator box of the power stage is preheated and caused to expand still before starting -the turbine,~so that no obstacle further hinders the expan-sion of the rotor in spite of the fact that the clear-ances between the stator and the rotor are kept to a minimum both under cold conditions and in steady opera-tion.
In addition, said preheating of the stator box is not carried out directly, but indirectly by conduction, inasmuch as another obJect of the present invention is also to i~prove the cooling in steady operat;on condi-tions of -the stator box and a direct heating of said box due to the presence of heating appliances, would make the attainment of the latter obJective both intrica-te and cumbersome.
On the other hand, a more efficient cooling of the stator box uhder steady operational conditions is required by the :intention of minimizing as ar as practi-cable the expansion of the stator box due to the tempera ture differential between the preheating temperature and the stead~ operational condition temperature, so as to minimize the clearances between the stator and the rotor under steady operational conditions and also to obtain beneficial results as to cons-truction economy and simplifi-cation since a cold stator box is not difficult to build and can be made with cheap steel alloys, that is, materials which are not too expensive. Also~ this improvement in cooling is then obtained, rather than by directly acting upon the stator box, in an indirect way by conduction.
According to the present invention there is pro~
vided a gas turbine, comprising a generator for the gas, a stator box of a power stage, an intermediate connection member having one end connected to said gas generator and another end connected to said stator box, heating means for externally heating said intermediate connection member, and annular chamber means provided internally to said intermediate connection memb~r within which cooling air is caused to flow along a helical path from a downstream end to an upstream end of said annular chamber.
According to a preferred embodiment of the present invention, there is provided a gas turbine comprisin~ a gas generator frontally and coaxially connected to an upstream end of an intermediate connection member, said intermediate connection member ha~ing a downstream end which is frontally and coaxially connected in heat-exchanging contact with a stator box of a power stage, said intermediate connection member supporting in correspondence with its upstream end a radial tube set for air intended to cool rotor discs of said power stage, said air being drawn under pressure from a compression stage of said gas generator, a heating electric coil embedded in the outer surface of said intermediate connection member, and an internal annular chamber provided inside said intermediate connection member and in the interior of which a set of ~nnular vertical gills define a helical pathway for said cooling air which is conveyed to the upstream end within said radial tube set from the downstream end of said chamber.
In summary, both the preheating and the subsequent improvement of the cooling of the stator bo~ of the gas turbine are obtained, according to the invention, by acting upon the intermediate connection member, or transition piece, which contacts thermally the stator box in the downstream section and is heated by an electric coil embedded therein, and is, conversely, cooled by an air stream under pressure drawn from a compression stage of the gas generator and helically conveyed within an annular chamber of said transi-tion piece in the direction from upstream to downstream thereof.
Preferably, the internal annular chamber of said intermediate connection member or transition piece is fed with said cooling air also in correspondence with its up-stream end, the two feeding streams, upstream and downstream, respectively, being governed by specially provided valves.
By so doing~ that is by properly calibrating said valves, the magnitude of the airflow for cooling, which flows through the chamber of the intermediate connection member, and thus the cooling of the stator box of the power stage can also be ad~usted.
- ~
/
a~
'71~
The invention is now more clearly illustrated with reference to the acoompanying drawings, which show a preferen-tial embodiment o-f a practical reduction to - practice which is given by way of example only and with-ou-t limitation, inasmuch as technical and constructional changes might be introduced at any rate without depart-ing from the scope of the present invention.
In the drawings -FIGURE 1 shows a side elevational view, par-tly in cross-section, of a gas turbine incor~orating the heat-exctlanger integrated with the stdtor box according to the teachings of the present Invention, and FIGURE ~ is a fragmentary side cross-sectional view on a considerably enlarged scale, of the heat-ex-changer shown in FIGURE 1.
Having now reference -to tne drawings, the numeral 1 generally indicates a gas turbine comprising an air-drawing casing 2 which supports the ups-tream end of a gas generator 3 ! the other end of which is secured to the upstream end 4', of an intermediate connection member, or transition piece~ 4, the lat-ter having a substantial-ly cylindrical outline. The downstream end, 4", of the member 4, in its turn1 is secured, by bolts such as 5, to the stator box 6, of the power stage 7, said box sup-porting the stator vanes 8, wllereas the rotor discs 9,mounted on the power shaft 10, of the stage 7, are cooled by the cooling air stream fed thereto through a radial tube set 11~ said tubes 11, being supported by the transi-`
7~
tion piece 4 in correspondence with the upstream end4', thereof.
FIGURE 1 shows, also, the diffuser 12, the exhaust box 13, and the piping 14 which conveys to the radial tubes 11 the air which has been drawn, under pressure, from a compression stage (in-termediate) of the gas gene-rator 3 aforesaid.
The cylindrical transition piec0 4, then, is equipped with an electric heating coil 15, embedded bodi-lQ ly in the outer surface of 4 and enclosed at its top byan annular insulating lid 16.
In its interior, the cylindrical piece 4 has, con-versely, an annular chamber 17, as well as a set of ver tical annular g:ills 18, which partition said chamber 17 into a number of annular chambers, referenced 171, 172, 173, 17~9 respectively, which are so serially and mutual-ly connected as to provide a helical pa!thway. The far-thest downstream chamber 171 is connected, via the regula-tion valve 19, to said piping 14 for conveying the cool~
ing air stream, whereas the nearest upstream chamber 174 communicates, via a set of bores 20, with the annular chamber 21 into which said radial tubes 11 open, and is connected to the piping 14 aforementioned through the regulation valve 22.
By so doing, the intermedia-te connection memberg : or transition piece 4, can act like a heat-exchanger for the stator box 6~ inasmuch as it~ for being hea-ted by the electric coil 15, will administer heat, through the an-.
.. . .
nular con-tact surface 23, to the stator box 6 which will therefore be heated whereas the same transition piece 4~ cooled by forced circulation of cooling air flowing from the annular chamber 171 to the annular chamber 21j will substrac-t heat from the stator chamber 6, still through said annular contact surface 23, whe-reby the stator box is cool.ed.
In order further to improve the magnitude of said heat exchange between the transition piece 4 and the stator box 6, the latter is constructed so as to have a small mass, whereby a small thermal inertia is achieved, whereas the central body and the downstream end 4" of the transition piece 4 are built massively to encourage thè
heat transfer therethrough and, lastly7 the aforesaid annular contact surface 23 is made very wide so as to encourage the heat exchange.
The present invention relates to a gas turbine having a heat-exchanger connected to its stator box.
In particular, the present invention relates to a heat-exchanger which is integrated with the stator box of a gas turbine, which, by permitting adequately to preheat said stator box prior to starting the turbine and then to cool it efficiently, makes also possible drastically to reduce the problems connected with the transient states of the gas ~urbine and thus to obtain high efficiencies in said turbines with lower costs and simpler constructional arrangements.
As is known, in a gas turbine and more particu larly in the power stage of a gas turbine high temperatures are experienced which originate considerable thermal expan-sions in the component parts concerned. However, while the rotorr Eor its having the vanes directly acted upon by the hot gases, expands immediately as the turbine is started, the stator box since its thickness is considerable, its position more external and subJected to more intense cooling, takes a longer time to become heated and thus to expand.
Thus, in order to prevent that during said tran-sient states the rotor portions, when expanded, may scrape the fixed stator portions with the possible atte:dan~
~'' /_._.
damages of the vanes andlor the sealing members, -the clearances between the ro-tor and the stator in the present gas turbines are held sufficiently wide and the result is a decrease of the efficiency of the tur-bine concerned.
The principal obJect of the present invention is thus to offset said defect and thus to provide a turbine having a high efficiency inasmuch as it becomes possible to keep narrow clearances between the rotor and -the sta-tor in the power stage.
Thls obJect is substantially achieved by virtueof the fact that the s-tator box of the power stage is preheated and caused to expand still before starting -the turbine,~so that no obstacle further hinders the expan-sion of the rotor in spite of the fact that the clear-ances between the stator and the rotor are kept to a minimum both under cold conditions and in steady opera-tion.
In addition, said preheating of the stator box is not carried out directly, but indirectly by conduction, inasmuch as another obJect of the present invention is also to i~prove the cooling in steady operat;on condi-tions of -the stator box and a direct heating of said box due to the presence of heating appliances, would make the attainment of the latter obJective both intrica-te and cumbersome.
On the other hand, a more efficient cooling of the stator box uhder steady operational conditions is required by the :intention of minimizing as ar as practi-cable the expansion of the stator box due to the tempera ture differential between the preheating temperature and the stead~ operational condition temperature, so as to minimize the clearances between the stator and the rotor under steady operational conditions and also to obtain beneficial results as to cons-truction economy and simplifi-cation since a cold stator box is not difficult to build and can be made with cheap steel alloys, that is, materials which are not too expensive. Also~ this improvement in cooling is then obtained, rather than by directly acting upon the stator box, in an indirect way by conduction.
According to the present invention there is pro~
vided a gas turbine, comprising a generator for the gas, a stator box of a power stage, an intermediate connection member having one end connected to said gas generator and another end connected to said stator box, heating means for externally heating said intermediate connection member, and annular chamber means provided internally to said intermediate connection memb~r within which cooling air is caused to flow along a helical path from a downstream end to an upstream end of said annular chamber.
According to a preferred embodiment of the present invention, there is provided a gas turbine comprisin~ a gas generator frontally and coaxially connected to an upstream end of an intermediate connection member, said intermediate connection member ha~ing a downstream end which is frontally and coaxially connected in heat-exchanging contact with a stator box of a power stage, said intermediate connection member supporting in correspondence with its upstream end a radial tube set for air intended to cool rotor discs of said power stage, said air being drawn under pressure from a compression stage of said gas generator, a heating electric coil embedded in the outer surface of said intermediate connection member, and an internal annular chamber provided inside said intermediate connection member and in the interior of which a set of ~nnular vertical gills define a helical pathway for said cooling air which is conveyed to the upstream end within said radial tube set from the downstream end of said chamber.
In summary, both the preheating and the subsequent improvement of the cooling of the stator bo~ of the gas turbine are obtained, according to the invention, by acting upon the intermediate connection member, or transition piece, which contacts thermally the stator box in the downstream section and is heated by an electric coil embedded therein, and is, conversely, cooled by an air stream under pressure drawn from a compression stage of the gas generator and helically conveyed within an annular chamber of said transi-tion piece in the direction from upstream to downstream thereof.
Preferably, the internal annular chamber of said intermediate connection member or transition piece is fed with said cooling air also in correspondence with its up-stream end, the two feeding streams, upstream and downstream, respectively, being governed by specially provided valves.
By so doing~ that is by properly calibrating said valves, the magnitude of the airflow for cooling, which flows through the chamber of the intermediate connection member, and thus the cooling of the stator box of the power stage can also be ad~usted.
- ~
/
a~
'71~
The invention is now more clearly illustrated with reference to the acoompanying drawings, which show a preferen-tial embodiment o-f a practical reduction to - practice which is given by way of example only and with-ou-t limitation, inasmuch as technical and constructional changes might be introduced at any rate without depart-ing from the scope of the present invention.
In the drawings -FIGURE 1 shows a side elevational view, par-tly in cross-section, of a gas turbine incor~orating the heat-exctlanger integrated with the stdtor box according to the teachings of the present Invention, and FIGURE ~ is a fragmentary side cross-sectional view on a considerably enlarged scale, of the heat-ex-changer shown in FIGURE 1.
Having now reference -to tne drawings, the numeral 1 generally indicates a gas turbine comprising an air-drawing casing 2 which supports the ups-tream end of a gas generator 3 ! the other end of which is secured to the upstream end 4', of an intermediate connection member, or transition piece~ 4, the lat-ter having a substantial-ly cylindrical outline. The downstream end, 4", of the member 4, in its turn1 is secured, by bolts such as 5, to the stator box 6, of the power stage 7, said box sup-porting the stator vanes 8, wllereas the rotor discs 9,mounted on the power shaft 10, of the stage 7, are cooled by the cooling air stream fed thereto through a radial tube set 11~ said tubes 11, being supported by the transi-`
7~
tion piece 4 in correspondence with the upstream end4', thereof.
FIGURE 1 shows, also, the diffuser 12, the exhaust box 13, and the piping 14 which conveys to the radial tubes 11 the air which has been drawn, under pressure, from a compression stage (in-termediate) of the gas gene-rator 3 aforesaid.
The cylindrical transition piec0 4, then, is equipped with an electric heating coil 15, embedded bodi-lQ ly in the outer surface of 4 and enclosed at its top byan annular insulating lid 16.
In its interior, the cylindrical piece 4 has, con-versely, an annular chamber 17, as well as a set of ver tical annular g:ills 18, which partition said chamber 17 into a number of annular chambers, referenced 171, 172, 173, 17~9 respectively, which are so serially and mutual-ly connected as to provide a helical pa!thway. The far-thest downstream chamber 171 is connected, via the regula-tion valve 19, to said piping 14 for conveying the cool~
ing air stream, whereas the nearest upstream chamber 174 communicates, via a set of bores 20, with the annular chamber 21 into which said radial tubes 11 open, and is connected to the piping 14 aforementioned through the regulation valve 22.
By so doing, the intermedia-te connection memberg : or transition piece 4, can act like a heat-exchanger for the stator box 6~ inasmuch as it~ for being hea-ted by the electric coil 15, will administer heat, through the an-.
.. . .
nular con-tact surface 23, to the stator box 6 which will therefore be heated whereas the same transition piece 4~ cooled by forced circulation of cooling air flowing from the annular chamber 171 to the annular chamber 21j will substrac-t heat from the stator chamber 6, still through said annular contact surface 23, whe-reby the stator box is cool.ed.
In order further to improve the magnitude of said heat exchange between the transition piece 4 and the stator box 6, the latter is constructed so as to have a small mass, whereby a small thermal inertia is achieved, whereas the central body and the downstream end 4" of the transition piece 4 are built massively to encourage thè
heat transfer therethrough and, lastly7 the aforesaid annular contact surface 23 is made very wide so as to encourage the heat exchange.
Claims (4)
1. A gas turbine, comprising:
- a generator for the gas, - a stator box of a power stage, - an intermediate connection member, having one end connected to said gas generator and another end connected to said stator box, - heating means for externally heating said intermediate connection member, and - annular chamber means provided internally to said intermediate connection member within which cooling air is caused to flow along a helical path from a downstream end to an upstream end of said annular chamber.
- a generator for the gas, - a stator box of a power stage, - an intermediate connection member, having one end connected to said gas generator and another end connected to said stator box, - heating means for externally heating said intermediate connection member, and - annular chamber means provided internally to said intermediate connection member within which cooling air is caused to flow along a helical path from a downstream end to an upstream end of said annular chamber.
2. A gas turbine, comprising:
- a generator for the gas, - a stator box of a power stage, - an intermediate connection member having an upstream end connected to a downstream end of said gas generator, and a downstream end coaxially connected to said stator box, - heating electric coil embedded in the outer surface of said intermediate connection member, and - an annular chamber provided internally to said intermediate connection member, wherein a set of annular vertical gills define a helical pathway for a cooling air which is conveyed from the downstream end to the upstream end of said intermediate connection member.
- a generator for the gas, - a stator box of a power stage, - an intermediate connection member having an upstream end connected to a downstream end of said gas generator, and a downstream end coaxially connected to said stator box, - heating electric coil embedded in the outer surface of said intermediate connection member, and - an annular chamber provided internally to said intermediate connection member, wherein a set of annular vertical gills define a helical pathway for a cooling air which is conveyed from the downstream end to the upstream end of said intermediate connection member.
3. A gas turbine comprising:
- a gas generator frontally and coaxially con-nected to an upstream end of an intermediate connection member, said intermediate connection member having a downstream end which is frontally and coaxially connected in heat-exchanging contact with a stator box of a power stage, - said intermediate connection member supporting in correspondence with its upstream end a radial tube set for air intended to cool rotor discs of said power stage, said air being drawn under pressure from a compression stage of said gas generator, - a heating electric coil embedded in the outer surface of said intermediate connection member, and - an internal annular chamber provided inside said intermediate connection member and in the interior of which a set of annular vertical gills define a helical pathway for said cooling air which is conveyed to the upstream end within said radial tube set from the downstream end of said chamber.
- a gas generator frontally and coaxially con-nected to an upstream end of an intermediate connection member, said intermediate connection member having a downstream end which is frontally and coaxially connected in heat-exchanging contact with a stator box of a power stage, - said intermediate connection member supporting in correspondence with its upstream end a radial tube set for air intended to cool rotor discs of said power stage, said air being drawn under pressure from a compression stage of said gas generator, - a heating electric coil embedded in the outer surface of said intermediate connection member, and - an internal annular chamber provided inside said intermediate connection member and in the interior of which a set of annular vertical gills define a helical pathway for said cooling air which is conveyed to the upstream end within said radial tube set from the downstream end of said chamber.
4. A gas turbine according to claim 1, character-ized in that said internal annular chamber of said interme-diate connection member is fed with said cooling air also in correspondence with its upstream end, the two feeding streams, upstream and downstream, respectively, being regulated by corresponding valves.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| IT23336A/81 | 1981-08-03 | ||
| IT23336/81A IT1137783B (en) | 1981-08-03 | 1981-08-03 | HEAT EXCHANGER INTEGRATED WITH THE STATIC CASE OF A GAS TURBINE |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1187809A true CA1187809A (en) | 1985-05-28 |
Family
ID=11206201
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000408572A Expired CA1187809A (en) | 1981-08-03 | 1982-08-02 | Heat-exchanger integrated with the stator box of a gas turbine |
Country Status (7)
| Country | Link |
|---|---|
| JP (1) | JPS5827803A (en) |
| CA (1) | CA1187809A (en) |
| DE (1) | DE3228799C2 (en) |
| FR (1) | FR2510656A1 (en) |
| GB (1) | GB2103718B (en) |
| IT (1) | IT1137783B (en) |
| SE (1) | SE8204552L (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11873758B1 (en) | 2022-10-28 | 2024-01-16 | Pratt & Whitney Canada Corp. | Gas turbine engine component with integral heat exchanger |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3407945A1 (en) * | 1984-03-03 | 1985-09-05 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | METHOD AND MEANS FOR AVOIDING THE DEVELOPMENT OF TITANIUM FIRE |
| FR2652858B1 (en) * | 1989-10-11 | 1993-05-07 | Snecma | TURBOMACHINE STATOR ASSOCIATED WITH MEANS OF DEFORMATION. |
| DE4327376A1 (en) * | 1993-08-14 | 1995-02-16 | Abb Management Ag | Compressor and method for its operation |
| US5667358A (en) * | 1995-11-30 | 1997-09-16 | Westinghouse Electric Corporation | Method for reducing steady state rotor blade tip clearance in a land-based gas turbine to improve efficiency |
| US6220814B1 (en) | 1998-07-16 | 2001-04-24 | Siemens Westinghouse Power Corporation | Turbine interstage sealing arrangement |
| DE10019437A1 (en) * | 2000-04-19 | 2001-12-20 | Rolls Royce Deutschland | Method and device for cooling the housings of turbines of jet engines |
| ATE446439T1 (en) | 2005-07-01 | 2009-11-15 | Siemens Ag | COOLED GAS TURBINE GUIDE BLADE FOR A GAS TURBINE, USE OF A GAS TURBINE GUIDE BLADE AND METHOD FOR OPERATING A GAS TURBINE |
| FR2943717B1 (en) * | 2009-03-27 | 2016-02-19 | Snecma | COMPRESSOR STATOR OR TURBINE ENGINE TURBINE FOR CONTROLLING THE AUTHORED GAME OF A ROTOR IN LOOK |
| FR2949808B1 (en) * | 2009-09-08 | 2011-09-09 | Snecma | PILOTAGE OF THE AUBES IN A TURBOMACHINE |
| EP2573332A1 (en) * | 2011-09-21 | 2013-03-27 | Siemens Aktiengesellschaft | Steam turbine having internal electric heating |
| US9057282B2 (en) * | 2011-11-22 | 2015-06-16 | General Electric Company | Systems and methods for adjusting clearances in turbines |
| US9151176B2 (en) | 2011-11-22 | 2015-10-06 | General Electric Company | Systems and methods for adjusting clearances in turbines |
| EP2664746A3 (en) * | 2012-05-16 | 2014-04-23 | General Electric Company | Systems and methods for adjusting clearances in turbines |
| EP2754859A1 (en) * | 2013-01-10 | 2014-07-16 | Alstom Technology Ltd | Turbomachine with active electrical clearance control and corresponding method |
| FR3002971B1 (en) * | 2013-03-06 | 2015-04-17 | Snecma | DEVICE FOR VENTILATION OF A STATOR CASE OF A TURBOMACHINE, COMPRISING AN ADJUSTMENT ON CIRCUMFERENCES |
| FR3002972B1 (en) * | 2013-03-06 | 2015-04-17 | Snecma | DEVICE FOR VENTILATION OF A STATOR CASING OF A TURBOMACHINE COMPRISING AN AXIAL ADJUSTMENT |
| RU2535453C1 (en) * | 2013-04-24 | 2014-12-10 | Николай Борисович Болотин | Gas turbine engine and method for radial clearance adjustment in gas turbine |
| RU2532737C1 (en) * | 2013-12-09 | 2014-11-10 | Николай Борисович Болотин | Gas turbine engine |
| US9702266B2 (en) * | 2014-06-30 | 2017-07-11 | Honeywell International Inc. | Turbocharger turbine housing |
| WO2019099009A1 (en) * | 2017-11-16 | 2019-05-23 | Siemens Aktiengesellschaft | Gas turbine clearance control system including embedded electrical heating circuitry |
| US11268403B2 (en) | 2018-01-05 | 2022-03-08 | Siemens Energy Global GmbH & Co. KG | Gas turbine engine induction system, corresponding induction heater and method for inductively heating a component |
| FR3109406B1 (en) | 2020-04-17 | 2022-10-07 | Safran Aircraft Engines | TURBINE CASE COOLING DEVICE |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| BE356074A (en) * | 1927-11-26 | |||
| CA1034510A (en) * | 1975-10-14 | 1978-07-11 | Westinghouse Canada Limited | Cooling apparatus for split shaft gas turbine |
| US4213296A (en) * | 1977-12-21 | 1980-07-22 | United Technologies Corporation | Seal clearance control system for a gas turbine |
| US4280792A (en) * | 1979-02-09 | 1981-07-28 | Avco Corporation | Air-cooled turbine rotor shroud with restraints |
-
1981
- 1981-08-03 IT IT23336/81A patent/IT1137783B/en active
-
1982
- 1982-07-30 FR FR8213306A patent/FR2510656A1/en active Granted
- 1982-08-02 SE SE8204552A patent/SE8204552L/en not_active Application Discontinuation
- 1982-08-02 GB GB08222302A patent/GB2103718B/en not_active Expired
- 1982-08-02 CA CA000408572A patent/CA1187809A/en not_active Expired
- 1982-08-02 DE DE3228799A patent/DE3228799C2/en not_active Expired
- 1982-08-03 JP JP57134817A patent/JPS5827803A/en active Granted
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11873758B1 (en) | 2022-10-28 | 2024-01-16 | Pratt & Whitney Canada Corp. | Gas turbine engine component with integral heat exchanger |
Also Published As
| Publication number | Publication date |
|---|---|
| IT1137783B (en) | 1986-09-10 |
| DE3228799A1 (en) | 1983-03-24 |
| JPS5827803A (en) | 1983-02-18 |
| SE8204552L (en) | 1983-02-04 |
| SE8204552D0 (en) | 1982-08-02 |
| FR2510656A1 (en) | 1983-02-04 |
| JPS6340241B2 (en) | 1988-08-10 |
| IT8123336A0 (en) | 1981-08-03 |
| DE3228799C2 (en) | 1984-05-10 |
| GB2103718B (en) | 1984-09-12 |
| GB2103718A (en) | 1983-02-23 |
| FR2510656B1 (en) | 1985-05-24 |
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| MKEC | Expiry (correction) | ||
| MKEX | Expiry |