US20080110593A1 - Cooling arrangement for electronics - Google Patents

Cooling arrangement for electronics Download PDF

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Publication number
US20080110593A1
US20080110593A1 US11/978,621 US97862107A US2008110593A1 US 20080110593 A1 US20080110593 A1 US 20080110593A1 US 97862107 A US97862107 A US 97862107A US 2008110593 A1 US2008110593 A1 US 2008110593A1
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US
United States
Prior art keywords
electrical component
fuel
cooling arrangement
aircraft
supply pipe
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.)
Abandoned
Application number
US11/978,621
Inventor
Michael H. Coney
Andrew J. Mullender
Brian A. Handley
David M. Parkin
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Assigned to ROLLS-ROYCE PLC reassignment ROLLS-ROYCE PLC ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: PARKIN, DAVID MICHAEL, HANDLEY, BRIAN ALEX, MULLENDER, ANDREW JAMES, CONEY, MICHAEL HARVEY
Publication of US20080110593A1 publication Critical patent/US20080110593A1/en
Abandoned legal-status Critical Current

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    • 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
    • F01D25/12—Cooling
    • 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
    • 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
    • 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

Definitions

  • the present invention relates to an arrangement for cooling electronic components, particularly but not exclusively, using fuel to cool an electronic control unit of a gas turbine engine.
  • Air-cooling of electronics is extensively used in industry. Indirect water cooling of electronics is also used for example in large computing environments and for processor cooling applications.
  • Air cooling is conventionally used in aero-gas turbine engines. This air cooling requires a controlled temperature environment to be effective and this has resulted in the use of an enclosure for the engine electronic control (EEC) on some of the Applicant's Trent® series of engines. Provision of the enclosure induces both cost and weight penalties.
  • EEC engine electronic control
  • an aircraft electrical component cooling arrangement comprises at least one electrical component housed in a body characterised in that fuel is passed through the body and directly over the component.
  • the component and body are of an engine's electronic control unit.
  • the body defines an inlet gallery and an outlet gallery for distribution of the fuel over the at least one electrical component.
  • the aircraft comprises a fuel supply pipe extending between a fuel tank and a combustor assembly, an inlet pipe connects from the fuel supply pipe to the body and the outlet pipe connects the body to the supply pipe.
  • a Venturi flow meter is provided in the supply pipe, the Venturi flow meter comprising a throat to which the outlet pipe is connected.
  • the arrangement comprises a pump and a fuel supply pipe extending from an aircraft fuel tank to the body.
  • the arrangement comprises a controllable valve for metering the flow of fuel into the body and temperature gauge for measuring the temperature of the components, the valve being controlled to maintain a desired temperature of the components.
  • the body is completely filled with fuel.
  • a method of operating an aircraft electrical component cooling arrangement comprising at least one electrical component housed in a body, the body connected to a fuel supply pipe, method is characterised by passing fuel through the body directly over the component to cool the component.
  • FIG. 1 is a schematic section of part of a ducted fan gas turbine engine attached to an aircraft structure
  • FIG. 2 is a schematic layout of an electrical component cooling arrangement in accordance with the present invention.
  • FIG. 3 is a section X-X through the electrical component cooling arrangement in accordance with the present invention.
  • a ducted fan gas turbine engine generally indicated at 10 has a principal and rotational axis XX.
  • the engine 10 is attached to the aircraft 9 , usually to a wing or fuselage, via a pylon 8 .
  • a fuel tank 29 is housed in the wing 9 .
  • the engine 10 comprises, in axial flow series, an air intake 11 , a propulsive fan 12 , an intermediate pressure compressor 13 , a high-pressure compressor 14 , combustion equipment 15 , a high-pressure turbine 16 , and intermediate pressure turbine 17 , a low-pressure turbine 18 and a core exhaust nozzle 19 .
  • a nacelle 21 generally surrounds the engine 10 and defines the intake 11 , a bypass duct 22 and a fan bypass exhaust nozzle 23 .
  • the gas turbine engine 10 works in the conventional manner so that air entering the intake 11 is accelerated by the fan 12 to produce two air flows: a first airflow A into the intermediate pressure compressor 13 and a second airflow B which passes through a bypass duct 22 to provide propulsive thrust.
  • the intermediate pressure compressor 13 compresses the airflow A directed into it before delivering that air to the high pressure compressor 14 where further compression takes place.
  • the compressed air exhausted from the high-pressure compressor 14 is directed into the combustion equipment 15 where it is mixed with fuel and the mixture combusted.
  • the resultant hot combustion products then expand through, and thereby drive the high, intermediate and low-pressure turbines 16 , 17 , 18 before being exhausted through the nozzle 19 to provide additional propulsive thrust.
  • the high, intermediate and low-pressure turbines 16 , 17 , 18 respectively drive the high and intermediate pressure compressors 14 , 13 and the fan 12 by suitable interconnecting shafts.
  • the fan 12 is circumferentially surrounded by a structural member in the form of a fan casing 24 , which is supported by an annular array of outlet guide vanes 25 .
  • Engine accessories such as the EEC 26 and oil tank are mounted on the fan casing 24 .
  • the EEC 26 generates a substantial amount of heat and therefore requires cooling to prevent component failure. As mentioned in the pre-amble most engine electronics are air cooled and duct ambient air for this purpose.
  • the cooling arrangement comprises the EEC 26 and a fuel supply pipe 28 and a pump 30 ; cooling pipes 32 connect the supply pipe 28 to an inlet pipe 32 and an outlet pipe 34 of the EEC 26 .
  • the pump is a Venturi flow meter through which the fuel flowing along the supply pipe 28 passes.
  • the outlet pipe 34 is connected at a throat 36 of the Venturi 30 and with the inlet pipe 32 connected to the supply pipe 28 upstream of the Venturi 30 , a flow of fuel passes through the EEC 26 .
  • the EEC 26 comprises a body 38 enclosing an array of electronic components 40 , such as capacitors, diodes, circuitry and microprocessors, and defines an inlet gallery 42 and an outlet gallery 44 to which the inlet and outlet pipes 32 , 34 are connected respectively.
  • electronic components 40 such as capacitors, diodes, circuitry and microprocessors
  • the electrical component cooling arrangement also comprises a controllable valve 48 for metering the flow of fuel into the body 38 and temperature gauge 50 for measuring the temperature of the components 40 , the valve 48 being controlled to maintain a desired temperature of the components 40 .
  • the temperature gauge 50 is attached to the body, but may be attached to an electrical component. A number temperature gauges may be attached to a number of components. Where the temperature of a component varies from its desired operation temperature more or less fuel may be supplied to the EEC.
  • the fuel supply pipe 28 is connected to an aircraft fuel tank and routed to injectors in the combustor assembly 15 .
  • the fuel supply pipe 28 is an additional connection to the aircraft fuel tank and the fuel from the outlet 34 is passed back to the tank.
  • the Venturi 30 is replaced by a convention pump 30 .
  • the temperature of the fuel used (Kerosene) operates at a generally even temperature and this permits a stable operating environment to be established for the electronics.
  • This use of fuel for controlling the environmental temperature is direct.
  • Direct cooling involves flooding all or part of the unit and electronic components with the Kerosene. As Kerosene and other fuels are dielectric there is no danger of the electrical components causing a fire hazard.
  • the advantages of the present invention are maintenance of a uniform temperature of the electronic components, protection against internal and external fire, ability to further miniaturise electrical components and/or combine units due to enhanced cooling effectiveness.
  • the word fuel is restricted to any dielectric petrochemical liquid.

Abstract

An aircraft electrical component cooling arrangement comprises at least one electrical component (40) housed in a body (38), for example an engine's electronic controller, characterised in that fuel is passed through the body (38) and directly over the component (40). Advantageously, this maintains a uniform temperature of the electronic components, protection against internal and external fire, ability to further miniaturise electrical components and/or combine units due to enhanced cooling effectiveness over convention air cooled systems.

Description

  • The present invention relates to an arrangement for cooling electronic components, particularly but not exclusively, using fuel to cool an electronic control unit of a gas turbine engine.
  • Air-cooling of electronics is extensively used in industry. Indirect water cooling of electronics is also used for example in large computing environments and for processor cooling applications.
  • Air cooling is conventionally used in aero-gas turbine engines. This air cooling requires a controlled temperature environment to be effective and this has resulted in the use of an enclosure for the engine electronic control (EEC) on some of the Applicant's Trent® series of engines. Provision of the enclosure induces both cost and weight penalties.
  • Therefore it is an object of the present invention to provide an electronic cooling arrangement that overcomes the above mentioned problems.
  • In accordance with the present invention an aircraft electrical component cooling arrangement comprises at least one electrical component housed in a body characterised in that fuel is passed through the body and directly over the component.
  • Preferably, the component and body are of an engine's electronic control unit.
  • Preferably, the body defines an inlet gallery and an outlet gallery for distribution of the fuel over the at least one electrical component.
  • Normally, the aircraft comprises a fuel supply pipe extending between a fuel tank and a combustor assembly, an inlet pipe connects from the fuel supply pipe to the body and the outlet pipe connects the body to the supply pipe.
  • Preferably, a Venturi flow meter is provided in the supply pipe, the Venturi flow meter comprising a throat to which the outlet pipe is connected.
  • Preferably, the arrangement comprises a pump and a fuel supply pipe extending from an aircraft fuel tank to the body.
  • Preferably, the arrangement comprises a controllable valve for metering the flow of fuel into the body and temperature gauge for measuring the temperature of the components, the valve being controlled to maintain a desired temperature of the components.
  • Preferably, the body is completely filled with fuel.
  • In another aspect of the present invention there is provided a method of operating an aircraft electrical component cooling arrangement comprising at least one electrical component housed in a body, the body connected to a fuel supply pipe, method is characterised by passing fuel through the body directly over the component to cool the component.
  • The present invention will be more fully described by way of example with reference to the accompanying drawings in which:
  • FIG. 1 is a schematic section of part of a ducted fan gas turbine engine attached to an aircraft structure;
  • FIG. 2 is a schematic layout of an electrical component cooling arrangement in accordance with the present invention;
  • FIG. 3 is a section X-X through the electrical component cooling arrangement in accordance with the present invention.
    •
  • Referring to FIG. 1, a ducted fan gas turbine engine generally indicated at 10 has a principal and rotational axis XX. The engine 10 is attached to the aircraft 9, usually to a wing or fuselage, via a pylon 8. Normally, a fuel tank 29 is housed in the wing 9.
  • The engine 10 comprises, in axial flow series, an air intake 11, a propulsive fan 12, an intermediate pressure compressor 13, a high-pressure compressor 14, combustion equipment 15, a high-pressure turbine 16, and intermediate pressure turbine 17, a low-pressure turbine 18 and a core exhaust nozzle 19. A nacelle 21 generally surrounds the engine 10 and defines the intake 11, a bypass duct 22 and a fan bypass exhaust nozzle 23.
  • The gas turbine engine 10 works in the conventional manner so that air entering the intake 11 is accelerated by the fan 12 to produce two air flows: a first airflow A into the intermediate pressure compressor 13 and a second airflow B which passes through a bypass duct 22 to provide propulsive thrust. The intermediate pressure compressor 13 compresses the airflow A directed into it before delivering that air to the high pressure compressor 14 where further compression takes place.
  • The compressed air exhausted from the high-pressure compressor 14 is directed into the combustion equipment 15 where it is mixed with fuel and the mixture combusted. The resultant hot combustion products then expand through, and thereby drive the high, intermediate and low- pressure turbines 16, 17, 18 before being exhausted through the nozzle 19 to provide additional propulsive thrust. The high, intermediate and low- pressure turbines 16, 17, 18 respectively drive the high and intermediate pressure compressors 14, 13 and the fan 12 by suitable interconnecting shafts.
  • The fan 12 is circumferentially surrounded by a structural member in the form of a fan casing 24, which is supported by an annular array of outlet guide vanes 25. Engine accessories such as the EEC 26 and oil tank are mounted on the fan casing 24.
  • The EEC 26 generates a substantial amount of heat and therefore requires cooling to prevent component failure. As mentioned in the pre-amble most engine electronics are air cooled and duct ambient air for this purpose.
  • Referring now to FIGS. 2 and 3, the present invention relates to using fuel to cool the EEC unit containing electronics. The cooling arrangement comprises the EEC 26 and a fuel supply pipe 28 and a pump 30; cooling pipes 32 connect the supply pipe 28 to an inlet pipe 32 and an outlet pipe 34 of the EEC 26. In this exemplary embodiment, the pump is a Venturi flow meter through which the fuel flowing along the supply pipe 28 passes. The outlet pipe 34 is connected at a throat 36 of the Venturi 30 and with the inlet pipe 32 connected to the supply pipe 28 upstream of the Venturi 30, a flow of fuel passes through the EEC 26.
  • The EEC 26 comprises a body 38 enclosing an array of electronic components 40, such as capacitors, diodes, circuitry and microprocessors, and defines an inlet gallery 42 and an outlet gallery 44 to which the inlet and outlet pipes 32, 34 are connected respectively.
  • The electrical component cooling arrangement also comprises a controllable valve 48 for metering the flow of fuel into the body 38 and temperature gauge 50 for measuring the temperature of the components 40, the valve 48 being controlled to maintain a desired temperature of the components 40. The temperature gauge 50 is attached to the body, but may be attached to an electrical component. A number temperature gauges may be attached to a number of components. Where the temperature of a component varies from its desired operation temperature more or less fuel may be supplied to the EEC.
  • When cooling of the EEC 26 is required fuel will flow into the EEC 26 and directly over the components 40. The chamber defined by the body 38 is completely filled with fuel. The fuel supply pipe 28 is connected to an aircraft fuel tank and routed to injectors in the combustor assembly 15. Alternatively, the fuel supply pipe 28 is an additional connection to the aircraft fuel tank and the fuel from the outlet 34 is passed back to the tank. In this case the Venturi 30 is replaced by a convention pump 30.
  • During a typical flight cycle, the temperature of the fuel used (Kerosene) operates at a generally even temperature and this permits a stable operating environment to be established for the electronics. This use of fuel for controlling the environmental temperature is direct. Direct cooling involves flooding all or part of the unit and electronic components with the Kerosene. As Kerosene and other fuels are dielectric there is no danger of the electrical components causing a fire hazard.
  • Due to the large thermal capacity of fuel (and other fluids compared to a gas), total immersion of the electronics provides the additional benefit of complete protection against fire attack external to the EEC 26.
  • Thus the advantages of the present invention are maintenance of a uniform temperature of the electronic components, protection against internal and external fire, ability to further miniaturise electrical components and/or combine units due to enhanced cooling effectiveness.
  • It should be appreciated by the skilled person that additional cooling of the electronic components or body 38 may be achieved by the use of ribs, fins, turbulators, pedestals (e.g. 46) and rotating fluid flow fields as known in the art.
  • In the context of the present invention the word fuel is restricted to any dielectric petrochemical liquid.

Claims (9)

1. An aircraft electrical component cooling arrangement comprises at least one electrical component housed in a body characterised in that fuel is passed through the body and directly over the component.
2. An aircraft electrical component cooling arrangement as claimed in claim 1 wherein the component and body are of an engine's electronic control unit.
3. An aircraft electrical component cooling arrangement as claimed in claim 1 wherein the body defines an inlet gallery and an outlet gallery for distribution of the fuel over the at least one electrical component.
4. An aircraft electrical component cooling arrangement as claimed in claim 1 wherein the aircraft comprises a fuel supply pipe extending between a fuel tank and a combustor assembly, an inlet pipe connects from the fuel supply pipe to the body and the outlet pipe connects the body to the supply pipe.
5. An aircraft electrical component cooling arrangement as claimed in claim 4 wherein a Venturi flow meter is provided in the supply pipe, the Venturi flow meter comprising a throat to which the outlet pipe is connected.
6. An aircraft electrical component cooling arrangement as claimed in claim 1 wherein the arrangement comprises a pump and a fuel supply pipe extending from an aircraft fuel tank to the body.
7. An aircraft electrical component cooling arrangement as claimed in claim 1 wherein the arrangement comprises a controllable valve for metering the flow of fuel into the body and temperature gauge for measuring the temperature of the components, the valve being controlled to maintain a desired temperature of the components.
8. An aircraft electrical component cooling arrangement as claimed in claim 1 wherein the body is completely filled with fuel.
9. A method of operating an aircraft electrical component cooling arrangement comprising at least one electrical component housed in a body, the body connected to a fuel supply pipe, method is characterised by passing fuel through the body directly over the component to cool the component.
US11/978,621 2006-11-11 2007-10-30 Cooling arrangement for electronics Abandoned US20080110593A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GBGB0622516.3A GB0622516D0 (en) 2006-11-11 2006-11-11 Cooling arrangement for electronics
GB0622516.3 2006-11-11

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EP (1) EP1921275A2 (en)
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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110139430A1 (en) * 2008-06-10 2011-06-16 Airbus Operations S.A.S. Heat dissipation system
US10618661B2 (en) * 2015-02-23 2020-04-14 Airbus Operations Gmbh On-board removable container for cooling cargo materials and equipment in aircraft
US11499485B2 (en) * 2020-02-10 2022-11-15 Raytheon Technologies Corporation Engine control device and methods thereof

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100192587A1 (en) * 2009-02-03 2010-08-05 William Kirk Hessler Combustor assembly for use in a gas turbine engine and method of assembling same

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5111280A (en) * 1988-11-10 1992-05-05 Iversen Arthur H Thermal management of power conditioning systems
US5692558A (en) * 1996-07-22 1997-12-02 Northrop Grumman Corporation Microchannel cooling using aviation fuels for airborne electronics
US6302190B1 (en) * 1998-06-30 2001-10-16 Cummins Engine Company Ltd. Cooling an engine control unit
US6352001B1 (en) * 1999-08-30 2002-03-05 General Electric Company Non-iterative method for obtaining mass flow rate
US6396692B1 (en) * 2000-07-27 2002-05-28 Motorola, Inc. Electronic control unit with integrated cooling module
US6434473B1 (en) * 1999-10-05 2002-08-13 Honda Giken Kogyo Kabushiki Kaisha Gas turbine aeroengine control system

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5111280A (en) * 1988-11-10 1992-05-05 Iversen Arthur H Thermal management of power conditioning systems
US5692558A (en) * 1996-07-22 1997-12-02 Northrop Grumman Corporation Microchannel cooling using aviation fuels for airborne electronics
US6302190B1 (en) * 1998-06-30 2001-10-16 Cummins Engine Company Ltd. Cooling an engine control unit
US6352001B1 (en) * 1999-08-30 2002-03-05 General Electric Company Non-iterative method for obtaining mass flow rate
US6434473B1 (en) * 1999-10-05 2002-08-13 Honda Giken Kogyo Kabushiki Kaisha Gas turbine aeroengine control system
US6396692B1 (en) * 2000-07-27 2002-05-28 Motorola, Inc. Electronic control unit with integrated cooling module

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110139430A1 (en) * 2008-06-10 2011-06-16 Airbus Operations S.A.S. Heat dissipation system
US10618661B2 (en) * 2015-02-23 2020-04-14 Airbus Operations Gmbh On-board removable container for cooling cargo materials and equipment in aircraft
US11499485B2 (en) * 2020-02-10 2022-11-15 Raytheon Technologies Corporation Engine control device and methods thereof

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Publication number Publication date
EP1921275A2 (en) 2008-05-14
GB0622516D0 (en) 2006-12-20

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Owner name: ROLLS-ROYCE PLC, GREAT BRITAIN

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:CONEY, MICHAEL HARVEY;MULLENDER, ANDREW JAMES;HANDLEY, BRIAN ALEX;AND OTHERS;REEL/FRAME:020076/0521;SIGNING DATES FROM 20071025 TO 20071029

STCB Information on status: application discontinuation

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