WO2017213526A1 - Dispositif de transfert de chaleur, carter de turbomachine, et support de stockage associé - Google Patents

Dispositif de transfert de chaleur, carter de turbomachine, et support de stockage associé Download PDF

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Publication number
WO2017213526A1
WO2017213526A1 PCT/PL2016/050027 PL2016050027W WO2017213526A1 WO 2017213526 A1 WO2017213526 A1 WO 2017213526A1 PL 2016050027 W PL2016050027 W PL 2016050027W WO 2017213526 A1 WO2017213526 A1 WO 2017213526A1
Authority
WO
WIPO (PCT)
Prior art keywords
fluid
inner cavity
lip
plug
aperture
Prior art date
Application number
PCT/PL2016/050027
Other languages
English (en)
Inventor
Wojciech Grzeszczak
Karol Filip Leszczynski
Robert Jacek Zreda
James William Vehr
Robert JAMIOLKOWSKI
Original Assignee
General Electric Company
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 General Electric Company filed Critical General Electric Company
Priority to CN201680086497.0A priority Critical patent/CN109563745B/zh
Priority to PCT/PL2016/050027 priority patent/WO2017213526A1/fr
Priority to JP2018563725A priority patent/JP6799083B2/ja
Priority to DE112016006941.3T priority patent/DE112016006941T5/de
Publication of WO2017213526A1 publication Critical patent/WO2017213526A1/fr

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
    • F01D25/14—Casings modified therefor
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid

Definitions

  • the present subject matter is related to turbomachines. More particularly, the present subject matter is directed to heat transfer in turbomachines.
  • Turbomachine systems are continuously being modified to increase efficiency and decrease cost.
  • One method for increasing the efficiency of a turbomachine system includes increasing the operating temperature of the turbomachine system.
  • the turbomachine system is constructed of materials which can withstand such temperatures during use.
  • a casing component within turbomachine systems, generally houses a nozzle/vane component (nozzle section).
  • a working fluid is channeled through the turbomachine system, via the nozzle section, toward a set of buckets/blades, which rotate to drive one or more outputs e.g., a dynamoelectric machine. Because the working fluid directly contacts the nozzle section, the heat from that working fluid often increases the temperature of the components in that nozzle section, causing them to expand. If the casing and the nozzle section are not sufficiently separated from one another, expansion of the nozzle section due to heating can cause rubbing with the casing, decreasing the turbomachine efficiency as well as reducing the lifespan of components in the turbomachine system.
  • Various embodiments include a heat transfer device, a turbomachine casing, and a related storage medium.
  • the device includes: a body having an outer surface and an inner cavity within the outer surface; at least one aperture extending through the body, the at least one aperture positioned to direct fluid from the inner cavity through the body to the outer surface; a first lip proximate a first end of the body, and a second lip proximate a second end of the body, the first lip and the second lip each extending radially outward from the outer surface relative to a direction of flow of the fluid through the inner cavity; and a plug coupled with the body, the plug for obstructing an end of the inner cavity, the plug positioned to redirect flow of the fluid from a first direction to a second, distinct direction.
  • a first aspect of the disclosure includes a device having: a body having an outer surface and an inner cavity within the outer surface; at least one aperture extending through the body, the at least one aperture positioned to direct fluid from the inner cavity through the body to the outer surface; a first lip proximate a first end of the body, and a second lip proximate a second end of the body, the first lip and the second lip each extending radially outward from the outer surface relative to a direction of flow of the fluid through the inner cavity; and a plug coupled with the body, the plug for obstructing an end of the inner cavity, the plug positioned to redirect flow of the fluid from a first direction to a second, distinct direction.
  • a second aspect of the disclosure includes a turbomachine casing including: an axial, flow path, the axial flow path including a first portion and a second portion axially downstream of the first portion; a nozzle cavity fluidly coupled with the axial flow path; a passageway fSuidly connecting the axial flow path and the nozzle cavity; and an impingement sleeve within the second portion of the axial flow path, the impingement sleeve including: a body having an outer surface and an inner cavity within the outer surface, wherein the inner cavity is f!uidly coupled with the first portion of the axial flow path; at least one aperture extending through the body, the at least one aperture positioned to direct fluid from the inner cavity through the body to the outer surface; and a first lip proximate a first end of the body, the first lip extending radially outward from the outer surface and sealing the first portion of the axial flow path from the second portion of the axial flow path.
  • a third aspect of the disclosure includes a non-transitory computer readable storage medium storing code representative of an device, the device physically generated upon execution of the code by a computerized additive manufacturing system, the code including: code representing the device, the device including: a body having an outer surface and an inner cavity within the outer surface; at least one aperture extending through the body, the at least one aperture positioned to direct fluid from the inner cavity through the body to the outer surface; a first iip proximate a first end of the body, and a second lip proximate a second end of the body, the first lip and the second lip each extending radially outward from the outer surface relative to a direction of flow of the fluid through the inner cavity; and a plug coupled with the body, the plug for obstructing an end of the inner cavity, the plug positioned to redirect flow of the fluid from a first direction to a second, distinct direction.
  • FIG. 1 shows a cross-sectional view of a device within an article, according to various embodiments of the di sclosure.
  • FIG. 2 shows a perspective view of the device of FIG. 1 , according to embodiments of the disclosure.
  • FIG. 3 is a schematic perspective view of a portion of a turbomachine including a device illustrating fluid flow according to various embodiments of the disclosure.
  • FIG. 4 is a schematic perspective view of a device within a turbomachine according to various embodiments of the disclosure.
  • FIG. 5 is a close-up depiction of a portion of the device of FIG. 4, according to various embodiments of the di sclosure.
  • FIG. 6 shows a block diagram of an additive manufacturing process including a non- transitory computer readable storage medium storing code representative of a template according to embodi ments of the disclosure.
  • a device e.g., impingement sleeve
  • casing e.g., turbomachine casing
  • Embodiments of the present disclosure may improve operation in a turbomachine (e.g., gas turbine or steam turbine), e.g., by increasing cooling efficiency, reducing cross flow, reducing cross flow degradation, reducing pressure loss, increasing backfiow mai'gins, providing increased heat transfer with reduced pressure drop, facilitating reuse of heat transfer fluid, facilitating series impingement cooling, increasing article life, facilitating use of increased system temperatures, increasing system efficiency, or a combination thereof.
  • a turbomachine e.g., gas turbine or steam turbine
  • FIGS. 1-2 illustrate one embodiment of an article 100 (FIGS. 1 ) and a device 200 (FIGS.
  • Article 100 and/or device 200 are formed according to any suitable manufacturing method. Suitable manufacturing methods include, but are not limited to. casting, machining, additive manufacturing, or a combination thereof.
  • additive manufacturing of device 200 may include direct metal laser melting (DMLM), direct metal laser sintering (DMLS), selective laser melting (SLM), selecti ve laser sintering (SLS), fused deposition modeling (FDM), three-dimensional (3D) printing, any other additive manufacturing technique, or a combination thereof.
  • DMLM direct metal laser melting
  • DMLS direct metal laser sintering
  • SLM selective laser melting
  • SLS selecti ve laser sintering
  • FDM fused deposition modeling
  • 3D three-dimensional
  • article 100 mciudes but is not limited to, a turbomachine casing (shell) 101 or component thereof.
  • a turbomachine casing 101 and the device 200 includes a curved and/or cylindrical impingement sleeve (impingement sleeve) 203.
  • Impingement sleeve 203 can include an elongated tube-shaped body 204 (FIG.
  • apertures 207 are configured to direct a heat transfer fluid (e.g., a gas or liquid) towards turbomachine casing 101 surrounding (cylindrical) impingement sleeve 203.
  • a heat transfer fluid e.g., a gas or liquid
  • apertures 207 are disposed circumferentially about body 204, and include apertures 207 which are axially adjacent one another (i.e., adjacent apertures 207 are disposed along the axis of fluid flow entering impingement sleeve 203).
  • apertures 207 can include substantially circular openings in body 204, however, in other embodiments, apertures 207 can include oblong, rectangular, polygonal, or other-shaped openings in body 204. In various embodiments, apertures 207 are approximately
  • apertures 207 may vary across body 204.
  • impingement sleeve 203 can include one or more fluid receiving features 209 formed in the outer surface 205 thereof.
  • Fluid receiving features 209 can include, e.g., one or more slots, holes, troughs or passageways allowing for movement of fluid therethrough, hi some cases, fluid receiving features 209 include a fluid directing feature, which directs flow of fluid (e.g., heat transfer fluid) away from apertures 207.
  • Apertures 207 are configured to direct the heat transfer fluid from an inner cavity 211 within cylindrical impingement sleeve 203, to curved outer surface 205 of impingement sleeve 203, and
  • inner cavity 211 can extend substantially entirely through the body of impingement sleeve 203 (along axial direction A. coinciding with the primary axis of the turbomachine in which casing 101 belongs, and primary axis of flow into the inlet 208 of inner cavity 211), and may terminate (dead-end) at a junction of the impingement sleeve 203 and adjacent plug 213.
  • FIG. 3 shows a schematic perspective view of turbomachine casing 101 and impingement sleeve 203, further illustrating fluid flow within casing 101 relative to impingement sleeve 203.
  • turbomachine casing 101 can include an axial flow path 103, located radially outboard of (radially farther from central axis of turbomachine) a nozzle cavity 105.
  • Nozzle cavity 105 can include a space proximate the turbomachine nozzles where heat transfer fluid is diverted to reduce a temperature difference between the inner nozzle section 107 of the turbomachine and the turbomachine casing 101.
  • axial flow path 103 include two portions: a first portion 103A and a second portion 103B axialiy downstream (farther from fluid inlet) of first portion and fluidly connected with first portion 103 A. Second portion 103B is shown partially filled in this depiction with impingement sleeve
  • Second portion 103B can have a larger inner diameter than first portion 103A, which may accommodate impingement sleeve 203.
  • impingement sleeve 203 can include a first lip 215 proximate a first end 217 and a second lip 219 proximate a second end 221 (opposite first end 217), In some cases, as shown in FIGS. 2 and 3, second lip 219 is coupled with plug 213 (e.g., within axial flow path 103), e.g., via force- fit, adhesive, coupling mechanism such as a screw, bolt, clamp, etc., welded and/or brazed connection, etc.
  • first lip 215 and second lip 219 include protrusions extending radially outward (relative to primary axis of fluid flow through inner cavity) from outer surface 205 of impingement sleeve 203.
  • first lip 215 and second lip 219 can define a circumferential space 115 between outer surface 205 of impingement sleeve 203 and an inner surface 117 of second portion 103B of cavity 103 (FIG. 4), such that the portions of impingement sleeve 203 extending between first lip 215 and second lip 219 do not contact the inner surface of second portion of 103B of cavity 203.
  • first lip 215 includes a circumferentially extending slot 223 which is sized to receive a seal (e.g., a seal ring) 225.
  • First lip 215, including seal ring 225, can fluidly seal second portion 103B of axial cavity 103 from first portion 103 A of axial cavity 103, such that the flow of heat transfer fluid 120 (e.g., gas such as air, or cooling liquid such as water) through first portion 103A is forced to flow axially into inner cavity of impingement sleeve 203.
  • heat transfer fluid 120 can flow through first portion 103 A of cavity 103, into impingement sleeve 203 (via internal cavity211, FIG.
  • This heat transfer fluid 120 may then be used for downstream or upstream operation, including additional heat transfer uses and/or integration with a working fluid, e.g.. hot gas.
  • a working fluid e.g.. hot gas.
  • impingement sleeve 203 need not include fluid receiving feature(s) 209 depicted in FIG. 2, given the fluid dynamics illustrated in FIG. 3. However, some embodiments may include fluid receiving feature(s) 209, which may extend axially within outer surface 205 and help to guide flow of heat transfer fluid 120 from apertures 207 toward passageway 230.
  • FIG. 4 shows a schematic depiction of another embodiment of an impingement sleeve 403, which includes a plug 413 (cross-sectional view shown) sealing second end 221 of sleeve 403, whereby plug 413 is matingly coupled with internal cavity 111 at second end 221 (e.g., portion of plug 413 fits within internal cavity 11 1).
  • plug 413 may include a portion that complements the opening within internal cavity 111 and matingly fits (e.g., force fit, compression fit, etc.) or couples with impingement sleeve 413.
  • Impingement sleeve 413 may not include a second lip 219 (FIG.
  • plug 413 may matingly engage directly with internal cavity 11 1, as opposed to contacting or otherwise coupling with second lip 219 (FIG. 3).
  • FIG. 5 shows a close-up view of plug 413 mated with second end 221.
  • plug 413 can include an internal aperture 415, e.g., for removal of plug 413 from impingement sleeve 403, and at least one circumferential slot 417, e.g., for receiving a seal member such as a seal ring or a retaining ring (e.g., for axially retaining impingement sleeve 403 and/or plug 413).
  • a seal member such as a seal ring or a retaining ring
  • heat transfer fluid 120 (e.g., depicted in FIG. 3) includes hot gas from another section of a turbomachine or another machine, which is routed to axial flow path 103 to help reduce the temperature differential between casing 101 and nozzle section 107. That is, while components within nozzle section 107 are subjected to high-temperature working fluid such as gas or steam, those components can heat up and expand. If the surrounding casing 101 does not heat as quickly, or to the same degree as nozzle section 107, one or more components within nozzle section 107 can interfere (e.g., rub, contact, etc.) with casing 101 and degrade performance of the machine.
  • high-temperature working fluid such as gas or steam
  • impingement sleeves 103, 403 can be implemented in casing 101 to enhance heat transfer in the casing 101 and decrease the differential, temperature between casing 101 and nozzle section.
  • heat transfer fluid 120 enters impingement sleeve 103 (or 403, FIG. 4) and flows axially in a first direction (e.g., substantially parallel with axis A). Due to its fluid velocity and direction, heat transfer fluid 120 may flow through impingement sleeve 303 and contact plug 213 (or plug 413, FIG. 3) which obstructs internal cavity 211 at its distal end (second end 221 of impingement sleeve 103).
  • Plug 213 may redirect (deflect) flow of heat transfer fluid 120 from the first direction to a second, distinct direction.
  • the second, distinct direction is distinct from the first direction of fluid flow by between approximately ninety degrees and approximately one-hundred-eighty degrees. That is, in some cases, flow of heat transfer fluid 120 is substantially reversed when contacting plug 213, 413 (e.g., having a substantially flat contact surface, or a substantially angled, concave or convex surface), which causes heat transfer fluid 120 to deflect back toward first end 217 of impingement sleeve 203, and also radially outward toward apertures 207. Heat transfer fluid 120 may further travel through apertures 207, around at least a portion of outer surface 205 of impingement sleeve 203, and into passageway
  • Impingement sleeve 203, 403 may be formed in a number of ways.
  • impingement sleeve 203, 403 may be formed by casting, machining, welding, extrusion, etc, hi one embodiment, however, additive manufacturing is particularly suited for manufacturing impingement sleeve 203, 403 (FIGS. 1 -6).
  • additive manufacturing may include any process of producing an object through the successive layering of material rather than the removal of material, which is the case with conventional processes. Additive manufacturing can create complex geometries without the use of any sort of tools, molds or fixtures, and with little or no waste material.
  • Additive manufacturing processes may include but are not limited to: 3D printing, rapid prototyping (RP), direct digital manufacturing (DDM), selective laser melting (SLM) and direct metal laser melting (DMLM).
  • RP rapid prototyping
  • DDM direct digital manufacturing
  • SLM selective laser melting
  • DMLM direct metal laser melting
  • FIG. 6 shows a schematic/block view of an illustrative computerized additive manufacturing system 900 for generating an object 902. in this example, system 900 is arranged for DMLM. It is understood that the general teachings of the disclosure are equally applicable to other forms of additive manufacturing.
  • Object 902 is illustrated as a double wailed turbomachine element; however, it is understood that the additive manufacturing process can be readily adapted to manufacture impingement sleeve 203, 403 (FIGS. 1-5).
  • AM system 900 generally includes a computerized additive manufacturing (AM) control system 904 and an AM printer 906.
  • AM computerized additive manufacturing
  • AM system 900 executes code 920 that includes a set of computer-executable instructions defining impingement sleeve 203, 403 (FIGS. 1-5) to physically generate the object using AM printer 906,
  • Each AM process may use different raw materials in the form of, for example, tine- grain powder, liquid (e.g., liquid metal), sheet, etc., a stock of which may be held in a chamber 910 of AM printer 906.
  • impingement sleeve 203, 403 (FIGS. 1-5) may be made of metal or similar materials.
  • an applicator 912 may create a thin layer of raw material 914 spread out as the blank canvas from which each successive slice of the final object will be created.
  • applicator 912 may directly apply or print the next layer onto a previous layer as defined by code 920, e.g., where the material is a metal.
  • a laser or electron beam 916 fuses particles for each slice, as defined by code 920, but this may not be necessary where a quick setting liquid metal is employed.
  • Various parts of AM printer 906 may move to accommodate the addition of each new layer, e.g., a build platform 918 may lower and/or chamber 910 and/or applicator 912 may rise after each layer.
  • AM control system 904 is shown implemented on computer 930 as computer program code.
  • computer 930 is shown including a memory 932, a processor 934, an input/output (I/O) interface 936, and a bus 938. Further, computer 930 is shown in communication with an external I/O device/resource 940 and a storage system 942.
  • processor 934 executes computer program code, such as AM control system 904, that is stored in memory 932 and/or storage system 942 under instructions from code 920 representative of impingement sleeve 203, 403 (FIGS. 1-5), described herein.
  • processor 934 can read and/or write data to/from memory 932, storage system 942, I/O device 940 and/or AM printer 906.
  • Bus 938 provides a communication link between each of the components in computer 930, and I/O device 940 can comprise any device that enables a user to interact with computer 940 (e.g., keyboard, pointing device, display, etc.).
  • Computer 930 is only representative of various possible combinations of hardware and software.
  • processor 934 may comprise a single processing unit, or be distributed across one or more processing units in one or more locations, e.g., on a client and server.
  • memory 932 and/or storage system 942 may reside at one or more physical locations.
  • Memory 932 and/or storage system 942 can comprise any combination of various types of non-transitory computer readable storage medium including magnetic media, optical media, random access memory (RAM), read only memory (ROM), etc.
  • Computer 930 can comprise any type of computing device such as a network server, a desktop computer, a laptop, a handheld device, a mobile phone, a pager, a personal data assistant, etc.
  • code 920 includes a set of computer- executable instructions defining outer electrode that can be used to physically generate the tip, upon execution of the code by system 900.
  • code 920 may include a precisely defined 3D model of outer electrode and can be generated from any of a large variety of well- known computer aided design (CAD) software systems such as AutoCAD®, TurboCAD®, DesignCAD 3D Max, etc.
  • CAD computer aided design
  • code 920 can take any now known or later developed file format.
  • code 920 may be in the Standard Tessellation Language (STL) which was created for stereolithography CAD programs of 3D Systems, or an additive manufacturing file (AMF), which is an American Society of Mechanical Engineers (ASME) standard that is an extensible markup-language (XML) based format designed to allow any CAD software to describe the shape and composition of any three-dimensional object to be fabricated on any AM printer.
  • STL Standard Tessellation Language
  • AMF additive manufacturing file
  • ASME American Society of Mechanical Engineers
  • XML extensible markup-language
  • Code 920 may be translated between different formats, converted into a set of data signals and transmitted, received as a set of data signals and converted to code, stored, etc., as necessary.
  • Code 920 may be an input to system 900 and may come from a part designer, an intellectual property (IP) provider, a design company, the operator or owner of system 900, or from other sources.
  • IP intellectual property
  • AM control system 904 executes code 920, dividing impingement sleeve 203, 403 (FIGS. 1-5) into a series of thin slices that it assembles using AM printer 906 in successive layers of liquid, powder, sheet or other material.
  • each layer is melted to the exact geometry defined by code 920 and fused to the preceding layer.
  • the impingement sleeve 203, 403 may be exposed to any variety of finishing processes, e.g., minor machining, sealing, polishing, assembly to other part of the i gniter tip, etc.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Powder Metallurgy (AREA)

Abstract

Divers modes de réalisation de la présente invention concernent un dispositif de transfert de chaleur, un carter de turbomachine et un support de stockage associé. Dans certains cas, le dispositif comprend : un corps présentant une surface externe et une cavité interne dans la surface externe ; au moins une ouverture s'étendant à travers le corps, ladite ouverture étant positionnée pour diriger un fluide de la cavité interne, à travers le corps, à la surface externe ; un premier rebord à proximité d'une première extrémité du corps, et un second rebord à proximité d'une seconde extrémité du corps, le premier rebord et le second rebord s'étendant chacun radialement vers l'extérieur depuis la surface externe par rapport à une direction d'écoulement du fluide à travers la cavité interne ; et un bouchon accouplé au corps, le bouchon servant à obstruer une extrémité de la cavité interne, le bouchon étant positionné pour rediriger l'écoulement du fluide d'une première direction à une seconde direction distincte.
PCT/PL2016/050027 2016-06-07 2016-06-07 Dispositif de transfert de chaleur, carter de turbomachine, et support de stockage associé WO2017213526A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
CN201680086497.0A CN109563745B (zh) 2016-06-07 2016-06-07 热传递装置、涡轮机壳体和相关存储介质
PCT/PL2016/050027 WO2017213526A1 (fr) 2016-06-07 2016-06-07 Dispositif de transfert de chaleur, carter de turbomachine, et support de stockage associé
JP2018563725A JP6799083B2 (ja) 2016-06-07 2016-06-07 熱伝達装置、ターボ機械ケーシング、および関連の記憶媒体
DE112016006941.3T DE112016006941T5 (de) 2016-06-07 2016-06-07 Wärmeübertragungsvorrichtung, Turbomaschinengehäuse und darauf bezogenes Lagermittel

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/PL2016/050027 WO2017213526A1 (fr) 2016-06-07 2016-06-07 Dispositif de transfert de chaleur, carter de turbomachine, et support de stockage associé

Publications (1)

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WO2017213526A1 true WO2017213526A1 (fr) 2017-12-14

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JP (1) JP6799083B2 (fr)
CN (1) CN109563745B (fr)
DE (1) DE112016006941T5 (fr)
WO (1) WO2017213526A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3101105A1 (fr) * 2019-09-23 2021-03-26 Safran Aircraft Engines Carter pour turbomachine et turbomachine équipée d’un tel carter

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013110765A1 (fr) * 2012-01-26 2013-08-01 Energy Intelligence Lab Gmbh Carter de turbine et de générateur refroidi en plusieurs parties
US20140341723A1 (en) * 2013-03-15 2014-11-20 General Electric Company Gas turbine vane insert to control particulate deposition
EP2863018A1 (fr) * 2013-10-17 2015-04-22 Alstom Technology Ltd Structure de refroidissement pour un conduit de transition d'une turbine à gaz
EP2960436A1 (fr) * 2014-06-27 2015-12-30 Alstom Technology Ltd Structure de refroidissement pour un conduit de transition d'une turbine à gaz

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Publication number Priority date Publication date Assignee Title
US9275364B2 (en) * 2011-11-02 2016-03-01 Sap Se Semantic configuration in a business process platform

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013110765A1 (fr) * 2012-01-26 2013-08-01 Energy Intelligence Lab Gmbh Carter de turbine et de générateur refroidi en plusieurs parties
US20140341723A1 (en) * 2013-03-15 2014-11-20 General Electric Company Gas turbine vane insert to control particulate deposition
EP2863018A1 (fr) * 2013-10-17 2015-04-22 Alstom Technology Ltd Structure de refroidissement pour un conduit de transition d'une turbine à gaz
EP2960436A1 (fr) * 2014-06-27 2015-12-30 Alstom Technology Ltd Structure de refroidissement pour un conduit de transition d'une turbine à gaz

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3101105A1 (fr) * 2019-09-23 2021-03-26 Safran Aircraft Engines Carter pour turbomachine et turbomachine équipée d’un tel carter

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CN109563745A (zh) 2019-04-02
JP2019521271A (ja) 2019-07-25
JP6799083B2 (ja) 2020-12-09
CN109563745B (zh) 2022-04-12
DE112016006941T5 (de) 2019-03-07

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