WO1997003281A1 - Prechauffage de combustible pour turbine a gaz a l'aide d'air de refroidissement comprime - Google Patents

Prechauffage de combustible pour turbine a gaz a l'aide d'air de refroidissement comprime Download PDF

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Publication number
WO1997003281A1
WO1997003281A1 PCT/US1996/007923 US9607923W WO9703281A1 WO 1997003281 A1 WO1997003281 A1 WO 1997003281A1 US 9607923 W US9607923 W US 9607923W WO 9703281 A1 WO9703281 A1 WO 9703281A1
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WO
WIPO (PCT)
Prior art keywords
passages
core
gas turbine
heat
compressed air
Prior art date
Application number
PCT/US1996/007923
Other languages
English (en)
Inventor
Scott Thorsten Cloyd
Stephen Walter Brown
Michael Scot Briesch
Original Assignee
Westinghouse Electric Corporation
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Westinghouse Electric Corporation filed Critical Westinghouse Electric Corporation
Publication of WO1997003281A1 publication Critical patent/WO1997003281A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F3/00—Plate-like or laminated elements; Assemblies of plate-like or laminated elements
    • F28F3/02—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
    • F28F3/04—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being integral with the element
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • F02C7/185—Cooling means for reducing the temperature of the cooling air or gas
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F02C7/224—Heating fuel before feeding to the burner
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
    • F28D9/00—Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
    • F28D9/0031—Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits for one heat-exchange medium being formed by paired plates touching each other
    • F28D9/0037—Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits for one heat-exchange medium being formed by paired plates touching each other the conduits for the other heat-exchange medium also being formed by paired plates touching each other
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F3/00—Plate-like or laminated elements; Assemblies of plate-like or laminated elements
    • F28F3/005—Arrangements for preventing direct contact between different heat-exchange media
    • 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
    • F05D2210/00—Working fluids
    • F05D2210/10—Kind or type
    • F05D2210/12—Kind or type gaseous, i.e. compressible

Definitions

  • the present invention relates to gas turbines. More specifically, the present invention relates to a system for capturing heat rejected from the portion of the compressor discharge air used to cool the turbine section of the gas turbine by transferring the heat to a fluid to be injected into the combustion section, such as gaseous fuel, without the use of an intermediate heat transfer fluid.
  • a gas turbine is comprised of three main components: a compressor section in which air is compressed, a combustion section in which the compressed air is heated by burning fuel and a turbine section in which the hot compressed gas from the combustion section is expanded.
  • this cooling is achieved by flowing relatively cool air over or within the turbine components. Since such cooling air must be pressurized to be effective, it is common practice to bleed a portion of the air discharged from the compressor section and divert it to the turbine components for cooling purposes. Although the cooling air eventually mixes with the hot gas expanding in the turbine, since it bypasses the combustion process much of the work expended in compressing the cooling air is not recovered in the expansion process. Consequently, to maximize the power output and efficiency of the gas turbine, it is desirable to minimize the quantity of cooling air used.
  • the air bled from the compressor is relatively hot -- i.e., 315-485°C (600-900°F) depending on the compression ratio. Consequently, the air bled from the compressor must often be cooled to ensure that its temperature is low enough to adequately cool the turbine components.
  • the quantity of air bled from the compressor for cooling purposes can be reduced by cooling the air prior to directing it to the turbine components, thereby increasing its capacity to absorb heat.
  • an air-to-air cooler was often used to cool the cooling air.
  • Another approach involves the use of dual shell and tube heat exchangers and an intermediate heat transfer fluid.
  • air bled from the compressor is cooled by transferring heat from the compressed air to an intermediate fluid, such as water, in a first heat exchanger.
  • the heat absorbed by the heat transfer fluid is then transferred to, for example, gaseous fuel in a second heat exchanger.
  • an intermediate fluid such as water
  • a gas turbine system having (i) a compressor section for producing compressed air, (ii) a combustion section for producing heated compressed gas by the combustion of a fuel in a first portion of the compressed air, (iii) a turbine section for expanding the heated compressed gas, and (iv) a heat exchanger having a core having means for cooling a second portion of the compressed air by (i) transferring heat from the compressed air to the core by convection,
  • the heat exchanger is a printed circuit type heat exchanger.
  • Figure 1 is a longitudinal cross-section, partially schematic, through a gas turbine system utilizing the compressed air cooling scheme of the current invention.
  • Figure 2 is an isometric view, partially cut away, of the heat exchanger shown in Figure 1.
  • Figure 3 is a cross-section through a portion of the heat exchanger core shown in Figure 2.
  • Figures 4-6 are plan views, partially schematic, of the plates shown in Figure 3 taken along lines IV-IV, V- V, and VI-VI, respectively.
  • FIG. 1 a longitudinal cross-section of a gas turbine system 1.
  • the gas turbine is comprised of three main components: a compressor section 2, a combustion section 3, and a turbine section 4.
  • a rotor 5 is centrally disposed in the gas turbine and extends through the three sections.
  • the compressor section 2 is comprised of a cylinder 6 that encloses altemating rows of stationary vanes 7 and rotating blades 8.
  • the stationary vanes 7 are affixed to the cylinder 6 and the rotating blades 8 are affixed to the rotor 5.
  • the combustion section 3 is comprised of a cylinder 9 which forms a chamber in which are disposed a plurality of combustors 10 and ducts 11 that connect the combustors to the turbine section 4.
  • a fuel supply pipe 23 is connected to a fuel manifold 24 that distributes fuel to a nozzle 25 in each combustor 10.
  • a portion of the rotor 5 extends through the combustion section 3 and is enclosed therein by a housing 12. Cooling air return pipes 13 and 14, discussed further below, penetrate the cylinder 9, extend through the chamber and terminate at a manifold 15 that surrounds a portion of the housing 12.
  • the turbine section 4 is comprised of an outer cylinder 16 that encloses an inner cylinder 17.
  • the inner cylinder 17 encloses alternating rows of stationary vanes 18 and rotating blades 19.
  • the stationary vanes 18 are affixed to the inner cylinder 17 and the rotating blades 19 are affixed to a plurality of rotating disks 20 that form the turbine section of the rotor 5.
  • the compressor inducts ambient air
  • the rotating blades 19 and disks 20 in the turbine section are exposed to the hot gas 27 from the combustors 10, which may be in excess of 1300°C (2370°F) , and are subjected to high stresses as a result of the centrifugal force imposed on them by their rotation. Since the ability of the materials that form the blades and disks to withstand stress decreases with increasing temperature, it is vital to provide adequate cooling to maintain the temperature of these components within allowable levels. In the preferred embodiment, this cooling is accomplished by diverting a portion 29 of the compressed air 22 from the chamber formed by the cylinder 9 to the turbine section of the rotor 5. This diversion is accomplished by bleeding air through an external bleed pipe 30 emanating from the cylinder 9.
  • the cooled cooling air 31 After being cooled, as explained below, the cooled cooling air 31 re-enters the gas turbine through return pipes 13 and 14.
  • the return pipes direct the air to the manifold 15 after which the cooling air penetrates the housing 12 through holes 50 and enters an annular gap 52 formed between the housing 12 and the rotor 5.
  • the cooling air 31 then enter the rotor 5 through holes 51 whereupon it flows through a plurality of intricate cooling passages (not shown) in the rotating disks and blades to achieve the desired cooling.
  • cooling air 29 bypasses the combustors 10. Even though this air ' eventually mixes with the hot gas expanding in the turbine section 4, the work recovered from the expansion of the compressed cooling air is much less than that recovered from the expansion of the compressed air heated in the combustors. In fact, as a result of losses due to pressure drop and mechanical efficiency, the work recovered from the cooling air is less than that required to compress the air in the compressor. Hence, the greater the quantity of cooling air used the less the net power output of the gas turbine.
  • the quantity of cooling air 29 bled from the compressor discharge 22 is reduced by cooling the air, thereby increasing its capacity to absorb heat from and cool the turbine components, without losing the rejected heat from the cycle.
  • This is accomplished by directing the hot cooling air 29 to a heat exchanger 53, which according to the current invention is preferably of the printed circuit heat exchanger type, as discussed more fully below.
  • the fuel 56 from a fuel source is also directed to the heat exchanger 53 via fuel supply piping 58.
  • the heated fuel 26 is returned to the gas turbine via piping 23.
  • the cooling air 29 is cooled by rejecting heat to the fuel 56, thereby heating the fuel. Since the heated fuel 26 is injected into and burned in the combustors 10, the heat it has absorbed from the cooling air 29 is returned to the cycle and reduces the quantity of fuel that must be burned to obtain the desired temperature of the gas 27 entering the turbine. Consequently, unlike traditional approaches to cooling the cooling air, the current invention does not result in significantly degrading the thermal efficiency of the gas turbine.
  • the heat exchanger 53 is of the printed circuit heat exchanger type ("PCHE") .
  • PCHE printed circuit heat exchanger type
  • Such heat exchangers are available from Heatric Ltd., Dorset, England and from Gencorp Aerojet, Collinso Cordova, CA.
  • the heat exchanger 53 is comprised of a housing 55 that encloses a core 54.
  • the heat exchanger housing 55 forms manifolds 61- 65.
  • Manifold 61 is connected to the hot compressed air piping 30. It receives the hot compressed air 29 supplied to the heat exchanger 53 and directs that air to the core 54.
  • Manifold 63 is connected to the cooled compressed air piping 40 and receives the cooled compressed air 31 from the core 54 that is to be discharged from the heat exchanger 53.
  • Manifold 64 is connected to the fuel supply piping 58. It receives the fuel 56 supplied to the heat exchanger 53 and directs the fuel to the core 54.
  • Manifold 62 is connected to the heated fuel piping 23 and receives the heated fuel 26 from the core 54 that is to be discharged from the heat exchanger 53.
  • the core 54 is formed from a solid mass, such as stainless steel, in which a large number of passages are formed.
  • the core 54 is preferably formed by a series of metal plates 44-46 that are interleaved and then diffusion bonded together along their planar surfaces.
  • the surfaces along which the plates were joined is indicated in Figure 3 by the dotted lines marked by reference numeral 37.
  • the plates 44-46 form a contiguous mass without intermediate boundaries.
  • each of the plates 44-46 contains a number of channels that were chemically milled into its surface prior to diffusion bonding using techniques similar to those used to form electrical printed circuits (hence the name "printed circuit heat exchanger").
  • the channels milled into plates 44 form passages 41 for the fuel 56, while the channels milled into plates 46 form passages 42 for the compressed air 29.
  • the plates 45 are sentinel plates, discussed further below.
  • the plates 44 alternate with plates 46 and, in the preferred embodiment, a sentinel plate 45 is disposed between each pair of plates 44 and 46.
  • the fuel passages 41 formed in plate 44 lie in a plane and extend along the entire length of the plate.
  • the inlets of the passages 41 are formed in one half of one end edge 68 of the plate 44 and the outlets are formed in the opposite half of the opposite end edge 69 of the plate.
  • the initial and final extent of the passages 41 are angled so that although the inlets and outlets of the passages are segregated into one half of the end edges 68 and 69, the major portions of the passages 41 are distributed over a major portion of the planar surface of the plate 44.
  • the manifold 64 creates a chamber 35 that serves to distribute the incoming fuel gas 56 to the passages 41.
  • the manifold 62 creates a chamber 32 that serves to collect the heated fuel gas 29 from the passages
  • the manifold 61 creates a chamber 33 that serves to distribute the incoming hot compressed air 29 to the passages 42.
  • the manifold 63 creates a chamber 34 that serves to collect the cooled compressed air 31 from the passages 42 for discharge from the heat exchanger 53.
  • the core 54 forms alternating parallel rows of fuel and compressed air passages that extend along its entire length, with each row of fuel passages 41 being sandwiched between two rows of compressed air passages 42.
  • the rows of passages 41 and 42 are arranged so that the fuel 56 and compressed air 29 flow in a counter flow arrangement.
  • a parallel flow arrangement could also be employed.
  • a cross flow arrangement in which the passages 41 and 42 were oriented perpendicular to each other, could also be employed.
  • the compressed air 29 flows through the passages 42 it transfers heat, primarily by convection -- that is, by heat transfer from a fluid to a solid --, to the adjacent portions of the core 54 that surround each of the passages 42. This heat is then transferred by conduction -- that is, by heat transfer through a solid -- to the adjacent portions of the core 54 that surround each of the passages 42. The heat is then transferred, primarily by convection, to the fuel 56 flowing through the passages 42. In this manner, heat is transferred from the compressed air 29 to the fuel 56 directly -- that is, without the use of an intermediate heat transfer fluid.
  • PCHE type heat exchanger eliminates the concern that an intermediate heat transfer fluid will enter the compressed air or fuel. Moreover, PCHE type heat exchangers are compact and have low pressure drops. In addition, due to the multitude of small passages in the core 54 through which the fuel and compressed air flow, the likelihood of a catastrophic leak, such as occurs when a tube fails in a shell and tube type heat exchanger, is minimized.
  • each sentinel plate 45 disposed between each pair of plates 44 and 46, as shown in Figure 3.
  • Channels milled into each sentinel plate 45 form a row of passages 43 disposed between the alternating rows of fuel passages 41 and compressed air passages 42.
  • the passages 43 formed in sentinel plate 45 lie in a plane and extend along the entire length of the plate.
  • One end of each passage 42 is formed in a portion of the side edge 74 of the plate 45 that is adjacent to the end edge 70.
  • Each passage 42 terminates in a dead end adjacent the other end edge 71 of the plate 45.
  • the sentinel passages 43 are angled so that the major portions of the passages are distributed over a major portion of the planar surface of the plate 45. As can be seen in Figure 3, the distance between a sentinel passage 43 and either a fuel passage 41 or compressed air passage 42 is shorter than the distance between a fuel passage and a compressed air passage. In the embodiment of the invention shown in Figure 1, the sentinel passages 43 are pressurized with an inert gas to a pressure higher than that of the fuel 56 or the compressed air 29.
  • the sentinel passages 43 may contain air at ambient pressure. This embodiment is shown in Figure 5. If fuel 56 enters a sentinel passage 43 it will flow into a chamber 36 formed by the manifold 65 and then into vent piping 49. A rise in the pressure in the vent piping 49, as sensed by a pressure sensor 57, will alert operating personnel to the presence of the leak so that appropriate corrective action can be undertaken before a dangerous situation arises.
  • a rupture disc 48 is installed in the vent piping 49 so that the fuel 56 will be vented to atmosphere when the pressure reaches a pre ⁇ determined level.
  • a hydrocarbon monitor could be installed in the compressed air piping 40 to allow detection of fuel leaks.
  • heat captured from the compressed air 29 is transferred to the fuel 56 that is injected into the combustors 11.
  • another fluid such as water or steam
  • the current invention may be utilized by directing water or steam, rather than fuel 56, through the heat exchanger 53.
  • the heated water or steam is injected into the combustors
  • auxiliary heat exchanger 66 shown in Figure 1, which may be a conventional air-to-air cooler of the fin-fan type over which ambient air 59 flows, that is connected in parallel with the heat exchanger 53.
  • the use of the auxiliary heat exchanger 66 will facilitate maintenance of the primary heat exchanger 53 without an extended outage of the gas turbine.
  • the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof and, accordingly, reference should be made to the appended claims, rather than to the foregoing specification, as indicating the scope of the invention.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Turbine à gaz qui possède un échangeur de chaleur (53) dans lequel la chaleur est prélevée dans de l'air comprimé et évacuée (30) de la section de compresseur qui est utilisée pour refroidir la partie turbine. Ledit échangeur de chaleur transfère de la chaleur de l'air de refroidissement à un fluide destiné à être réinjecté dans la section de combustion de la turbine à gaz, tel que du combustible, sans recours à un fluide de transfert de chaleur intermédiaire. La chaleur prélevée de l'air de refroidissement est renvoyée dans le cycle lorsque le fluide est introduit dans la chambre de combustion de la turbine à gaz. Ledit échangeur de chaleur est du type circuit imprimé et possède une partie centrale constituée par un certain nombre de plaques liées par diffusion le long de leurs surfaces planes. Des canaux ménagés dans la surface des plaques avant le collage forment des passages dans lesquels circulent l'air de refroidissement et le fluide d'injection.
PCT/US1996/007923 1995-07-10 1996-05-28 Prechauffage de combustible pour turbine a gaz a l'aide d'air de refroidissement comprime WO1997003281A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US49985195A 1995-07-10 1995-07-10
US08/499,851 1995-07-10

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WO1997003281A1 true WO1997003281A1 (fr) 1997-01-30

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Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1997044575A1 (fr) * 1996-05-17 1997-11-27 Westinghouse Electric Corporation Systeme de refroidissement d'air a boucle fermee pour turbines a combustion
EP0919707A1 (fr) * 1997-12-01 1999-06-02 Asea Brown Boveri AG Refroidisseur à air froid pour turbines à gaz
EP1063401A1 (fr) * 1999-06-25 2000-12-27 ABB Alstom Power (Schweiz) AG Appareil et procédé pour séparer l'air d'un liquide
EP1074708A1 (fr) * 1999-06-25 2001-02-07 ABB Alstom Power (Schweiz) AG Appareil de séparation gaz-liquide
EP1132699A1 (fr) * 2000-03-06 2001-09-12 Air Products And Chemicals, Inc. Procédé et installation de chauffage d'oxygène liquide pompée
FR2935473A1 (fr) * 2008-08-27 2010-03-05 Air Liquide Echangeur de chaleur.
WO2014008005A1 (fr) * 2012-07-02 2014-01-09 United Technologies Corporation Echange d'énergie thermique de turbomachine
WO2014122890A1 (fr) * 2013-02-06 2014-08-14 株式会社神戸製鋼所 Échangeur de chaleur
US9045998B2 (en) 2011-12-12 2015-06-02 Honeywell International Inc. System for directing air flow to a plurality of plena
JP2015105760A (ja) * 2013-11-28 2015-06-08 株式会社前川製作所 熱交換器
US20150240722A1 (en) * 2014-02-21 2015-08-27 Rolls-Royce Corporation Single phase micro/mini channel heat exchangers for gas turbine intercooling
US9267390B2 (en) 2012-03-22 2016-02-23 Honeywell International Inc. Bi-metallic actuator for selectively controlling air flow between plena in a gas turbine engine
US9422063B2 (en) 2013-05-31 2016-08-23 General Electric Company Cooled cooling air system for a gas turbine
US9429072B2 (en) 2013-05-22 2016-08-30 General Electric Company Return fluid air cooler system for turbine cooling with optional power extraction
EP2664766A3 (fr) * 2012-05-16 2018-04-04 Rolls-Royce plc Échangeur thermique
EP3715603A1 (fr) * 2019-03-29 2020-09-30 Hamilton Sundstrand Corporation Échangeur de chaleur à combustible doté d'une barrière
US11208954B2 (en) * 2014-02-21 2021-12-28 Rolls-Royce Corporation Microchannel heat exchangers for gas turbine intercooling and condensing
EP4130635A1 (fr) * 2021-08-05 2023-02-08 Airbus SAS Échangeur thermique limitant les risques de contamination entre deux fluides et aéronef comprenant au moins un tel échangeur thermique
WO2024002522A1 (fr) 2022-06-30 2024-01-04 Linde Gmbh Échangeur de chaleur à ailettes en plaques, procédé de production d'un échangeur de chaleur à ailettes en plaques et procédé d'utilisation d'un échangeur de chaleur à ailettes en plaques

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3570593A (en) * 1968-02-05 1971-03-16 Trane Soc Heat-exchanger
US3926251A (en) * 1973-02-16 1975-12-16 Owens Illinois Inc Recuperator structures
EP0212878A1 (fr) * 1985-08-08 1987-03-04 Heatric Pty. Limited Echangeur de chaleur à plaques et à courant croisé
US5255505A (en) * 1992-02-21 1993-10-26 Westinghouse Electric Corp. System for capturing heat transferred from compressed cooling air in a gas turbine
EP0584958A1 (fr) * 1992-08-03 1994-03-02 General Electric Company Refroidissement des aubes de turbine par air réfrigeré

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3570593A (en) * 1968-02-05 1971-03-16 Trane Soc Heat-exchanger
US3926251A (en) * 1973-02-16 1975-12-16 Owens Illinois Inc Recuperator structures
EP0212878A1 (fr) * 1985-08-08 1987-03-04 Heatric Pty. Limited Echangeur de chaleur à plaques et à courant croisé
US5255505A (en) * 1992-02-21 1993-10-26 Westinghouse Electric Corp. System for capturing heat transferred from compressed cooling air in a gas turbine
EP0584958A1 (fr) * 1992-08-03 1994-03-02 General Electric Company Refroidissement des aubes de turbine par air réfrigeré

Cited By (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1997044575A1 (fr) * 1996-05-17 1997-11-27 Westinghouse Electric Corporation Systeme de refroidissement d'air a boucle fermee pour turbines a combustion
EP0919707A1 (fr) * 1997-12-01 1999-06-02 Asea Brown Boveri AG Refroidisseur à air froid pour turbines à gaz
EP1063401A1 (fr) * 1999-06-25 2000-12-27 ABB Alstom Power (Schweiz) AG Appareil et procédé pour séparer l'air d'un liquide
EP1074708A1 (fr) * 1999-06-25 2001-02-07 ABB Alstom Power (Schweiz) AG Appareil de séparation gaz-liquide
US6375718B1 (en) 1999-06-25 2002-04-23 Alstom (Switzerland) Ltd Apparatus and process for gas/liquid separation
EP1132699A1 (fr) * 2000-03-06 2001-09-12 Air Products And Chemicals, Inc. Procédé et installation de chauffage d'oxygène liquide pompée
US6360561B2 (en) 2000-03-06 2002-03-26 Air Products And Chemicals, Inc. Apparatus and method of heating pumped liquid oxygen
FR2935473A1 (fr) * 2008-08-27 2010-03-05 Air Liquide Echangeur de chaleur.
US9045998B2 (en) 2011-12-12 2015-06-02 Honeywell International Inc. System for directing air flow to a plurality of plena
US9267390B2 (en) 2012-03-22 2016-02-23 Honeywell International Inc. Bi-metallic actuator for selectively controlling air flow between plena in a gas turbine engine
EP2664766A3 (fr) * 2012-05-16 2018-04-04 Rolls-Royce plc Échangeur thermique
WO2014008005A1 (fr) * 2012-07-02 2014-01-09 United Technologies Corporation Echange d'énergie thermique de turbomachine
US9086019B2 (en) 2012-07-02 2015-07-21 United Technologies Corporation Turbomachine thermal energy exchange
JP2014152963A (ja) * 2013-02-06 2014-08-25 Kobe Steel Ltd 熱交換器
WO2014122890A1 (fr) * 2013-02-06 2014-08-14 株式会社神戸製鋼所 Échangeur de chaleur
US9429072B2 (en) 2013-05-22 2016-08-30 General Electric Company Return fluid air cooler system for turbine cooling with optional power extraction
US9422063B2 (en) 2013-05-31 2016-08-23 General Electric Company Cooled cooling air system for a gas turbine
JP2015105760A (ja) * 2013-11-28 2015-06-08 株式会社前川製作所 熱交換器
US20150240722A1 (en) * 2014-02-21 2015-08-27 Rolls-Royce Corporation Single phase micro/mini channel heat exchangers for gas turbine intercooling
US10316750B2 (en) * 2014-02-21 2019-06-11 Rolls-Royce North American Technologies, Inc. Single phase micro/mini channel heat exchangers for gas turbine intercooling
US11208954B2 (en) * 2014-02-21 2021-12-28 Rolls-Royce Corporation Microchannel heat exchangers for gas turbine intercooling and condensing
EP3715603A1 (fr) * 2019-03-29 2020-09-30 Hamilton Sundstrand Corporation Échangeur de chaleur à combustible doté d'une barrière
US11035616B2 (en) 2019-03-29 2021-06-15 Hamilton Sundstrand Corporation Fuel heat exchanger with a barrier
US11713929B2 (en) 2019-03-29 2023-08-01 Hamilton Sundstrand Corporation Fuel heat exchanger with a barrier
EP4130635A1 (fr) * 2021-08-05 2023-02-08 Airbus SAS Échangeur thermique limitant les risques de contamination entre deux fluides et aéronef comprenant au moins un tel échangeur thermique
US20230044493A1 (en) * 2021-08-05 2023-02-09 Airbus Sas Heat exchanger limiting the risk of contamination between two fluids and aircraft comprising at least one such heat exchanger
FR3126034A1 (fr) * 2021-08-05 2023-02-10 Airbus (S.A.S.) Echangeur thermique limitant les risques de contamination entre deux fluides et aéronef comprenant au moins un tel échangeur thermique
WO2024002522A1 (fr) 2022-06-30 2024-01-04 Linde Gmbh Échangeur de chaleur à ailettes en plaques, procédé de production d'un échangeur de chaleur à ailettes en plaques et procédé d'utilisation d'un échangeur de chaleur à ailettes en plaques

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