GB2476253A - Fuel Injector Cooled by a Heat Pipe - Google Patents
Fuel Injector Cooled by a Heat Pipe Download PDFInfo
- Publication number
- GB2476253A GB2476253A GB0921958A GB0921958A GB2476253A GB 2476253 A GB2476253 A GB 2476253A GB 0921958 A GB0921958 A GB 0921958A GB 0921958 A GB0921958 A GB 0921958A GB 2476253 A GB2476253 A GB 2476253A
- Authority
- GB
- United Kingdom
- Prior art keywords
- fuel
- feed arm
- heat pipe
- fuel injector
- heat
- 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.)
- Withdrawn
Links
- 239000000446 fuel Substances 0.000 title claims abstract description 70
- 239000012530 fluid Substances 0.000 claims abstract description 27
- 238000002485 combustion reaction Methods 0.000 claims abstract description 6
- 230000008021 deposition Effects 0.000 claims description 6
- 238000001816 cooling Methods 0.000 claims description 4
- 239000000843 powder Substances 0.000 description 11
- 239000007921 spray Substances 0.000 description 10
- 238000000151 deposition Methods 0.000 description 6
- 239000000155 melt Substances 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 238000009835 boiling Methods 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 239000000758 substrate Substances 0.000 description 2
- 230000032258 transport Effects 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 230000004888 barrier function Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000000571 coke Substances 0.000 description 1
- 238000004939 coking Methods 0.000 description 1
- 238000010894 electron beam technology Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
Classifications
-
- 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
- F28D15/00—Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls ; Heat-exchange apparatus employing intermediate heat-transfer medium or bodies
- F28D15/02—Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls ; Heat-exchange apparatus employing intermediate heat-transfer medium or bodies in which the medium condenses and evaporates, e.g. heat pipes
- F28D15/04—Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls ; Heat-exchange apparatus employing intermediate heat-transfer medium or bodies in which the medium condenses and evaporates, e.g. heat pipes with tubes having a capillary structure
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
- F23D14/78—Cooling burner parts
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/36—Details, e.g. burner cooling means, noise reduction means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
-
- 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
- F28D15/00—Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls ; Heat-exchange apparatus employing intermediate heat-transfer medium or bodies
- F28D15/02—Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls ; Heat-exchange apparatus employing intermediate heat-transfer medium or bodies in which the medium condenses and evaporates, e.g. heat pipes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2214/00—Cooling
-
- 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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E20/00—Combustion technologies with mitigation potential
- Y02E20/30—Technologies for a more efficient combustion or heat usage
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A fuel injector for a gas turbine engine has an injector head which directs the fuel into a combustion chamber of the engine, and a feed arm which extends from a casing of the engine to the injector head and which includes an internal passage for the transport of fuel to the injector head. The fuel injector has a heat pipe which extends along the feed arm to transfer heat from a high temperature region of the feed arm to a low temperature region located in a bypass airstream of the engine outside the casing. The fuel injector also has a heat exchanger at the low temperature region for dissipating heat transferred by the heat pipe into the bypass airstream. The heat pipe may surround the internal passage of the feed arm, and may include a wick portion and a fluid cavity portion extending parallel to each other along the feed arm. The heat exchanger may include several fins located in the bypass airstream, for example a dedicated bypass airstream, or a fan bypass duct airstream.
Description
FUEL INJECTOR
The present invention relates to a fuel injector for a gas turbine engine.
In a gas turbine engine, fuel injectors are used to deliver fuel to the combustion chamber. Typically, the fuel injector protrudes through a casing of the engine. On the external side of the casing, fuel is received into the injector from a fuel manifold, the received fuel then travels to the interior of the casing along an internal passage in a feed arm of the injector, eventually to arrive at an injector head which accepts the fuel from the feed arm and delivers it in a suitable form to the combustion chamber. For example, a fuel injector having a io fuel spray nozzle injector head atomises the fuel to ensure its rapid evaporation and burning when mixed with air.
Between the casing and the combustion chamber, the fuel injector is exposed to a flow of heat from the compressed air discharge by the high pressure (HP) compressor of the engine. Conventional fuel injectors use is passive heatshields to restrict the flow of heat from the HP compressor discharge to the relatively cool fuel. For example, a system of concentric cavities may be arranged to provide trapped air gaps between an exterior heatshield part washed with compressor air and an interior fuel transfer tube in contact with the fuel.
A problem arises, however, that, for a given compressor discharge temperature, the temperature difference between the exterior heatshield part and the interior fuel transfer tube is largely determined by the flow of fuel through the injector. That is, the injector relies for cooling on the flow of fuel, which imposes a top limit to the compressor discharge temperature that can be tolerated.
Further layers of heatshield can be added, but the benefit quickly outweighs the extra complexity.
Thus it would be desirable to provide a fuel injector which facilitates more active thermal management.
Accordingly, the present invention provides in a first aspect a fuel injector for a gas turbine engine, the fuel injector having: an injector head which directs the fuel into a combustion chamber of the engine, and a feed arm which extends from a casing of the engine to the injector head, the feed arm having an internal passage for the transport of fuel to the injector head; wherein the fuel injector further has: a heat pipe which extends along the feed arm to transfer heat from a high temperature region of the feed arm to a low temperature region located in a bypass airstream of the engine outside the casing, and a heat exchanger at the low temperature region for dissipating heat transferred by the heat pipe into the bypass airstream.
Advantageously, the heat pipe can extract heat from the feed arm and delivers the extracted heat to the bypass airstream. Thus heat is removed from the feed arm other than by the flow of fuel through the injector. This allows the injector to operate in a more arduous environment. For example, higher HP compressor exit air temperatures and/or higher fuel inlet temperatures to the injector can be permitted. Also the heat pipe can be tailored to target regions of the injector known to experience high fuel-wetted wall temperatures, thereby reducing fuel coking and enhancing on-wing life.
The fuel injector may have any one or, to the extent they are compatible, any combination of the following optional features.
Typically, the heat pipe surrounds the internal passage of the feed arm, for example in a coaxial arrangement. The heat pipe can thus act as a continuously cooled heatshield.
The heat pipe may extend to the injector head to transfer heat therefrom.
For example, the heat pipe may surround the injector head.
Typically, the heat pipe has a fluid wick portion and a vapour passage portion, the fluid wick and vapour cavity portions extending parallel to each other along the feed arm, with the vapour cavity portion being located externally of the fluid wick portion. An advantage of this arrangement is that the vapour cavity portion tends to offer better heat transfer resistance then the fluid wick portion.
Conveniently, a fluid wick portion of the heat pipe can be formed by direct energy beam deposition, for example by direct laser deposition. Such a deposition approach allows a fluid wick portion with a complex shape to be produced. It can also result fluid wick portion with integral, porous channels through which the working fluid can be transported by capillary action.
The heat exchanger may comprise a plurality of cooling fins which are located in the bypass airstream. The engine may be configured to direct a dedicated bypass airstream to the heat exchanger, or the heat exchanger may be located in an existing bypass duct of the engine, for example a fan bypass duct.
The present invention provides in a second aspect, a gas turbine engine having one or more fuel injectors according to the first aspect. The fuel injectors io may have any one or, to the extent they are compatible, any combination of the optional features of the first aspect.
Embodiments of the invention will now be described by way of example with reference to the accompanying drawings in which: Figure 1 shows a schematic longitudinal section through a heat pipe; and Figure 2 shows a schematic longitudinal section through a fuel injector.
Figure 1 shows a schematic longitudinal section through a heat pipe 1.
The heat pipe has a casing 2, a wick layer 3 and a vapour cavity 4. A working fluid is contained in the pipe by the casing. The left hand end of the pipe is hot and the right hand end is cold. The working fluid in the vapour cavity evaporates at hot end pipe, absorbing thermal energy. The vapour migrates along the vapour cavity to the cold end of the pipe, where the vapour condenses back into liquid releasing thermal energy. The condensed liquid is absorbed by the wick layer and flows back to the hot end of the pipe under capillary action. The cycle then repeats. In Figure 1, arrows indicate the movement of fluid.
Figure 2 shows a schematic longitudinal section through a fuel injector 5 according to an embodiment of the present invention. The fuel injector has a fuel feed arm 6 which extends from a casing (not shown) of a gas turbine engine to an air spray nozzle 7 where fuel is atomised and injected into the combustor (not shown) of the engine. The fuel for the air spray nozzle is conveyed down a fuel transfer tube 8 which extends along the axis of the feed arm.
The end of the feed arm 6 distal from the air spray nozzle 7 penetrates through the casing. Fuel is delivered into the fuel transfer tube 8 from a fuel manifold (not shown) on the exterior of the casing, the manifold also delivering fuel to other fuel injectors.
Compressed air (indicated by arrows A) discharged by the HP compressor enters the air spray nozzle 7 to atomise the fuel, but also impinges on the feed arm 6 and the body of the air spray nozzle. The impinging air heats the fuel injector. Some of the heat is carried away by the fuel flow through the injector. However, to allow increased fuel and compressed air temperatures, and to avoid excessive fuel-wetted wall temperatures in the injector (which can lead to hot spots and coke formation), the fuel injector has a heat pipe comprising a fluid wick portion 9 and a vapour cavity portion 10. These portions extend the length of the feed arm, surrounding the fuel transfer tube 8, with the vapour cavity portion located externally of the fluid wick portion. They also extend around the outer surface of the air spray nozzle.
The heat pipe transports heat away from hot regions of the feed arm 6 and the air spray nozzle 7 towards the cold end of the heat pipe, which is located outside the casing and is therefore not exposed to the compressed air discharged by the HP compressor. Indeed, the cold end of the heat pipe terminates at a heat exchanger 11 formed at the end of the feed arm. The heat exchanger is situated in a bypass airstream (indicated by arrow B) and has cooling fins aligned with the direction of the airstream, allowing heat to be removed by the heat pipe and dissipated in the airstream.
The vapour cavity portion 10 of the heat pipe is exterior of the fluid wick portion 9, as the vapour cavity portion tends to provide a better barrier to heat transfer than the fluid wick portion.
The heat pipe can be configured to cover more or less of the feed arm 6 and the air spray nozzle 7 as needed.
The fluid used in the heat pipe changes state from liquid to vapour at the appropriate temperature, which for fuel injector applications is typically around 160°C. The fluid can be water, the boiling point of which can be adjusted by controlling the pressure within the heat pipe. For example, water at 5 bar has a boiling point of around 16000 and at 8 bar a boiling point of around 175°C.
For some engines, the bypass airstrearri can be the air flow through an existing bypass duct, such as a fan bypass duct. In these cases, although there would be a pressure loss penalty in the bypass duct due to the presence of the heat exchanger, there would be no net heat loss from the engine.
One option for producing the fluid wick portion 9 is to use a direct energy beam deposition manufacturing technique. Direct laser deposition (DLD) is a commonly used example of the technique, although other energy beams, such as electron beams, can be used in an equivalent manner. In DLD a laser is used to melt a powder or wire at a selected location. As the melt solidifies it leaves a deposit having a height. By repeatedly depositing and melting at a location the height of the deposit can be built up. In this way, a complex structure such as the fluid wick portion may be formed on e.g. the fuel transfer tube and/or an appropriate wall of the air spray nozzle 7.
One DLD approach uses a powder bed where a level layer of powder is provided on an indexing base. The laser scans over the layer of powder and selectively melts regions of the powder. The base is indexed vertically and a is new layer of powder added, the depth of the layer being equal to or less than the depth of melt that can be achieved by the laser, before the laser is re-scanned to melt powder in the new layer. The melted powder joins with the previous layer as determined by the two melt patterns. The process then continues to form further layers. In another DLD approach, which may be more suitable for forming the fluid wick portion 9, a laser head is used into which a powder stream is directed. The power stream intersects with the focus of the laser beam on the surface of the substrate. The laser melts a pool into the substrate and the powder is melted and deposited into the pool. As the laser traverses from the location of the melt pool, the melted powder cools and solidifies until the next traverse where a portion of the deposit is re-melted to form a new melt pool.
By appropriate selection of the DLD conditions the fluid wick portion 9 can be formed with integral, porous channels through which the working fluid can be transported by capillary action.
While the invention has been described in conjunction with the exemplary embodiments described above, many equivalent modifications and variations will be apparent to those skilled in the art when given this disclosure. Accordingly, the exemplary embodiments of the invention set forth above are considered to be illustrative and not limiting. Various changes to the described embodiments may be made without departing from the spirit and scope of the invention.
Claims (8)
- CLAIMS1. A fuel injector (5) for a gas turbine engine, the fuel injector having: an injector head (7) which directs the fuel into a combustion chamber of the engine, and a feed arm (6) which extends from a casing of the engine to the injector head, the feed arm having an internal passage (8) for the transport of fuel to the injector head; wherein the fuel injector further has: a heat pipe which extends along the feed arm to transfer heat from a high temperature region of the feed arm to a low temperature region located in a bypass airstream of the engine outside the casing, and a heat exchanger (11) at the low temperature region for dissipating heat transferred by the heat pipe into the bypass airstream.
- 2. A fuel injector according to claim 1, wherein heat pipe surrounds the internal passage of the feed arm.
- 3. A fuel injector according to claim 1 or 2, wherein the heat pipe extends to the injector head to transfer heat therefrom.
- 4. A fuel injector according to any one of the previous claims, wherein the heat pipe has a fluid wick portion (9) and a vapour cavity portion (10), the fluid wick and vapour cavity portions extending parallel to each other along the feed arm, with the vapour cavity portion being located externally of the fluid wick portion.
- 5. A fuel injector according to any one of the previous claims, wherein a fluid wick portion of the heat pipe is formed by direct energy beam deposition.
- 6. A fuel injector according to any one of the previous claims, wherein the heat exchanger comprises a plurality of cooling fins which are located in the bypass airstream.
- 7. A gas turbine engine having one or more fuel injectors according to any one of the previous claims.
- 8. A fuel injector as any one herein described with reference to and/or as shown in Figure 2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB0921958A GB2476253A (en) | 2009-12-17 | 2009-12-17 | Fuel Injector Cooled by a Heat Pipe |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB0921958A GB2476253A (en) | 2009-12-17 | 2009-12-17 | Fuel Injector Cooled by a Heat Pipe |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB0921958D0 GB0921958D0 (en) | 2010-02-03 |
| GB2476253A true GB2476253A (en) | 2011-06-22 |
Family
ID=41717026
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB0921958A Withdrawn GB2476253A (en) | 2009-12-17 | 2009-12-17 | Fuel Injector Cooled by a Heat Pipe |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2476253A (en) |
Cited By (24)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2846092A3 (en) * | 2013-09-07 | 2015-03-25 | Messer Austria GmbH | Burner |
| CN105202577A (en) * | 2014-06-25 | 2015-12-30 | 中航商用航空发动机有限责任公司 | Fuel nozzle and combustor |
| EP2971684A4 (en) * | 2013-03-14 | 2016-03-09 | United Technologies Corp | Hollow-wall heat shield for fuel injector component |
| EP3199871A1 (en) * | 2016-01-28 | 2017-08-02 | Rolls-Royce North American Technologies, Inc. | Heat exchanger integrated with fuel nozzle |
| EP3260780A1 (en) * | 2016-06-20 | 2017-12-27 | United Technologies Corporation | Gas turbine combustor injector with heat pipe cooling |
| US9909448B2 (en) | 2015-04-15 | 2018-03-06 | General Electric Company | Gas turbine engine component with integrated heat pipe |
| EP3447382A1 (en) * | 2017-08-25 | 2019-02-27 | Delavan, Inc. | Heat transfer arrangements and method of making heat transfer arrangements |
| US10356945B2 (en) | 2015-01-08 | 2019-07-16 | General Electric Company | System and method for thermal management using vapor chamber |
| US10365047B2 (en) | 2016-06-21 | 2019-07-30 | Ge Aviation Systems Llc | Electronics cooling with multi-phase heat exchange and heat spreader |
| US10660236B2 (en) | 2014-04-08 | 2020-05-19 | General Electric Company | Systems and methods for using additive manufacturing for thermal management |
| US10775046B2 (en) | 2017-10-18 | 2020-09-15 | Rolls-Royce North American Technologies Inc. | Fuel injection assembly for gas turbine engine |
| US10830150B2 (en) | 2016-01-28 | 2020-11-10 | Rolls-Royce Corporation | Fuel heat exchanger with leak management |
| FR3106373A1 (en) * | 2020-01-20 | 2021-07-23 | Safran Aircraft Engines | INJECTOR FOR A TURBOMACHINE |
| US11118784B2 (en) | 2016-01-28 | 2021-09-14 | Rolls-Royce North American Technologies Inc. | Heat exchanger integrated with fuel nozzle |
| US11260953B2 (en) | 2019-11-15 | 2022-03-01 | General Electric Company | System and method for cooling a leading edge of a high speed vehicle |
| US11260976B2 (en) | 2019-11-15 | 2022-03-01 | General Electric Company | System for reducing thermal stresses in a leading edge of a high speed vehicle |
| US11267551B2 (en) | 2019-11-15 | 2022-03-08 | General Electric Company | System and method for cooling a leading edge of a high speed vehicle |
| US11352120B2 (en) | 2019-11-15 | 2022-06-07 | General Electric Company | System and method for cooling a leading edge of a high speed vehicle |
| US11407488B2 (en) | 2020-12-14 | 2022-08-09 | General Electric Company | System and method for cooling a leading edge of a high speed vehicle |
| US11427330B2 (en) | 2019-11-15 | 2022-08-30 | General Electric Company | System and method for cooling a leading edge of a high speed vehicle |
| US11519332B1 (en) | 2021-05-11 | 2022-12-06 | Rolls-Royce North American Technologies Inc. | Fuel injector with integrated heat exchanger for use in gas turbine engines |
| US11577817B2 (en) | 2021-02-11 | 2023-02-14 | General Electric Company | System and method for cooling a leading edge of a high speed vehicle |
| US11745847B2 (en) | 2020-12-08 | 2023-09-05 | General Electric Company | System and method for cooling a leading edge of a high speed vehicle |
| US12040690B2 (en) | 2020-08-31 | 2024-07-16 | General Electric Company | Cooling a stator housing of an electric machine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4052144A (en) * | 1976-03-31 | 1977-10-04 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Fuel combustor |
| GB2109916A (en) * | 1981-11-04 | 1983-06-08 | Combustion Eng | Nozzle cooled by heat pipe means |
| US4736693A (en) * | 1987-07-31 | 1988-04-12 | Shell Oil Company | Partial combustion burner with heat pipe-cooled face |
| EP1884625A2 (en) * | 2006-07-28 | 2008-02-06 | General Electric Company | Heat transfer system and method for turbine engine using heat pipes |
-
2009
- 2009-12-17 GB GB0921958A patent/GB2476253A/en not_active Withdrawn
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4052144A (en) * | 1976-03-31 | 1977-10-04 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Fuel combustor |
| GB2109916A (en) * | 1981-11-04 | 1983-06-08 | Combustion Eng | Nozzle cooled by heat pipe means |
| US4736693A (en) * | 1987-07-31 | 1988-04-12 | Shell Oil Company | Partial combustion burner with heat pipe-cooled face |
| EP1884625A2 (en) * | 2006-07-28 | 2008-02-06 | General Electric Company | Heat transfer system and method for turbine engine using heat pipes |
Cited By (32)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2971684A4 (en) * | 2013-03-14 | 2016-03-09 | United Technologies Corp | Hollow-wall heat shield for fuel injector component |
| US9920693B2 (en) | 2013-03-14 | 2018-03-20 | United Technologies Corporation | Hollow-wall heat shield for fuel injector component |
| EP3401529A1 (en) * | 2013-03-14 | 2018-11-14 | United Technologies Corporation | Hollow-wall heat shield for fuel injector component |
| EP2846092A3 (en) * | 2013-09-07 | 2015-03-25 | Messer Austria GmbH | Burner |
| US10660236B2 (en) | 2014-04-08 | 2020-05-19 | General Electric Company | Systems and methods for using additive manufacturing for thermal management |
| CN105202577A (en) * | 2014-06-25 | 2015-12-30 | 中航商用航空发动机有限责任公司 | Fuel nozzle and combustor |
| CN105202577B (en) * | 2014-06-25 | 2017-10-20 | 中国航发商用航空发动机有限责任公司 | Fuel nozzle and combustion chamber |
| US10356945B2 (en) | 2015-01-08 | 2019-07-16 | General Electric Company | System and method for thermal management using vapor chamber |
| US9909448B2 (en) | 2015-04-15 | 2018-03-06 | General Electric Company | Gas turbine engine component with integrated heat pipe |
| US10830147B2 (en) | 2016-01-28 | 2020-11-10 | Rolls-Royce North American Technologies Inc. | Heat exchanger integrated with fuel nozzle |
| US11118784B2 (en) | 2016-01-28 | 2021-09-14 | Rolls-Royce North American Technologies Inc. | Heat exchanger integrated with fuel nozzle |
| EP3199871A1 (en) * | 2016-01-28 | 2017-08-02 | Rolls-Royce North American Technologies, Inc. | Heat exchanger integrated with fuel nozzle |
| US10830150B2 (en) | 2016-01-28 | 2020-11-10 | Rolls-Royce Corporation | Fuel heat exchanger with leak management |
| EP3260780A1 (en) * | 2016-06-20 | 2017-12-27 | United Technologies Corporation | Gas turbine combustor injector with heat pipe cooling |
| US10458331B2 (en) * | 2016-06-20 | 2019-10-29 | United Technologies Corporation | Fuel injector with heat pipe cooling |
| US10365047B2 (en) | 2016-06-21 | 2019-07-30 | Ge Aviation Systems Llc | Electronics cooling with multi-phase heat exchange and heat spreader |
| US11035621B2 (en) | 2016-06-21 | 2021-06-15 | Ge Aviation Systems Llc | Electronics cooling with multi-phase heat exchange and heat spreader |
| US11994290B2 (en) | 2017-08-25 | 2024-05-28 | Collins Engine Nozzles, Inc. | Heat transfer arrangements and methods of making heat transfer arrangements |
| US11073282B2 (en) | 2017-08-25 | 2021-07-27 | Delavan Inc. | Gas turbine combustion liner comprising heat transfer cell heat pipes |
| EP3447382A1 (en) * | 2017-08-25 | 2019-02-27 | Delavan, Inc. | Heat transfer arrangements and method of making heat transfer arrangements |
| US10775046B2 (en) | 2017-10-18 | 2020-09-15 | Rolls-Royce North American Technologies Inc. | Fuel injection assembly for gas turbine engine |
| US11260953B2 (en) | 2019-11-15 | 2022-03-01 | General Electric Company | System and method for cooling a leading edge of a high speed vehicle |
| US11260976B2 (en) | 2019-11-15 | 2022-03-01 | General Electric Company | System for reducing thermal stresses in a leading edge of a high speed vehicle |
| US11267551B2 (en) | 2019-11-15 | 2022-03-08 | General Electric Company | System and method for cooling a leading edge of a high speed vehicle |
| US11352120B2 (en) | 2019-11-15 | 2022-06-07 | General Electric Company | System and method for cooling a leading edge of a high speed vehicle |
| US11427330B2 (en) | 2019-11-15 | 2022-08-30 | General Electric Company | System and method for cooling a leading edge of a high speed vehicle |
| FR3106373A1 (en) * | 2020-01-20 | 2021-07-23 | Safran Aircraft Engines | INJECTOR FOR A TURBOMACHINE |
| US12040690B2 (en) | 2020-08-31 | 2024-07-16 | General Electric Company | Cooling a stator housing of an electric machine |
| US11745847B2 (en) | 2020-12-08 | 2023-09-05 | General Electric Company | System and method for cooling a leading edge of a high speed vehicle |
| US11407488B2 (en) | 2020-12-14 | 2022-08-09 | General Electric Company | System and method for cooling a leading edge of a high speed vehicle |
| US11577817B2 (en) | 2021-02-11 | 2023-02-14 | General Electric Company | System and method for cooling a leading edge of a high speed vehicle |
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|---|---|
| GB0921958D0 (en) | 2010-02-03 |
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