GB720012A - Improvements in or relating to the cooling of aircraft propulsion plants - Google Patents

Improvements in or relating to the cooling of aircraft propulsion plants

Info

Publication number
GB720012A
GB720012A GB9442/51A GB944251A GB720012A GB 720012 A GB720012 A GB 720012A GB 9442/51 A GB9442/51 A GB 9442/51A GB 944251 A GB944251 A GB 944251A GB 720012 A GB720012 A GB 720012A
Authority
GB
United Kingdom
Prior art keywords
fuel
pump
heat exchanger
hot
engine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
GB9442/51A
Inventor
George Frederick Pitts
Arthur Harry Oliver Brown
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.)
Bristol Aeroplane Co Ltd
Original Assignee
Bristol Aeroplane Co Ltd
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 Bristol Aeroplane Co Ltd filed Critical Bristol Aeroplane Co Ltd
Priority to GB9442/51A priority Critical patent/GB720012A/en
Publication of GB720012A publication Critical patent/GB720012A/en
Expired legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00Features, 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
    • F02C7/04Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/047Heating to prevent icing
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/08Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D37/00Arrangements in connection with fuel supply for power plant
    • B64D37/02Tanks

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Temperature-Responsive Valves (AREA)

Abstract

720,012. Gas turbine plant. BRISTOL AEROPLANE CO., Ltd. April 23, 1952 [April 23, 1951], No. 9442/51. Class 110 (3). [Also in Group XXXIV] A gas turbine plant burning liquid fuel has means for circulating liquid fuel in a circuit in heat exchange relation with parts requiring heating and cooling respectively and means for replenishing the fuel in the circuit with fresh fuel from the fuel storage means to make up for normal losses of fuel from the circuit and to prevent the return of fuel to the storage means. Fuel from a tank 5 is supplied by a booster pump 6 to the main engine fuel pump 9 through a filter 7. Fuel is bled from the conduit between the filter 7 and pump 9 and passed through a non-return valve 10, a heat exchanger 13 and a chamber 11 for separating the air and vapour from the fuel to a further pump 17. The fuel is heated in the heat exchanger 13 by the hot lubricating oil from the engine. The valve 10 closes in the flow direction if the flow exceeds a predetermined amount. The flow of hot fuel from the pump 17 is divided into three paths 19, 20 and 21. One path 19 passes through the heating jacket of the filter before joining the inlet of the heat exchanger 13 at 23. The other two paths 20, 21 pass to two annular distributing chambers 24, 25 disposed around the air intake to the compressor 27. From the chamber 25, the fuel flows through the guide blades 28 to another annular chamber 29 and from thence into the jacket space 30 of a doublewalled intake bullet fairing 31. The fuel flows from the chamber 24 through spaces 32 of the leading edge fairings 33 of the intake spider to the space 30. The combined flow from the space 30 passes through the space 35 of a hollow intake spider arm and the conduit 36 to the point 23. To control the rate of heat transfer throttle valves 37, 38 are provided, these valves may be controlled by manual, thermostatic or ice-detecting means. When thermostatic control is provided, the thermostat may be placed in the heating or cooling part of the engine, depending on which is the more critical. Additional heat exchangers 39, 40 may be employed. These heat exchangers may use hot gas as a heating medium or may bring the fuel into contact with the hot external or internal parts of the engine. In this case, the heat exchanger 13 may be omitted. There is a possibility of the fuel being overheated where additional heat exchangers are used. In this case, some of the hot fuel may be returned to the fuel system through a conduit 41, a throttle valve 42 and a venturi 43 and the valve 10 over-ridden so that it may pass more fuel. The matrix of the heat exchanger 13, the pump 17 and driving motor 18 may be assembled to form a unit which may be mounted on the wall of the lubricating oil storage tank above the oil level. The motor 18 may be a turbine driven by air bled from the compressor. The invention may be applied to a plant with several engines.
GB9442/51A 1951-04-23 1951-04-23 Improvements in or relating to the cooling of aircraft propulsion plants Expired GB720012A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB9442/51A GB720012A (en) 1951-04-23 1951-04-23 Improvements in or relating to the cooling of aircraft propulsion plants

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB9442/51A GB720012A (en) 1951-04-23 1951-04-23 Improvements in or relating to the cooling of aircraft propulsion plants

Publications (1)

Publication Number Publication Date
GB720012A true GB720012A (en) 1954-12-08

Family

ID=9872036

Family Applications (1)

Application Number Title Priority Date Filing Date
GB9442/51A Expired GB720012A (en) 1951-04-23 1951-04-23 Improvements in or relating to the cooling of aircraft propulsion plants

Country Status (1)

Country Link
GB (1) GB720012A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2536842A1 (en) * 1982-11-29 1984-06-01 Gen Electric ENGINE LUBRICATING OIL HEAT RECOVERY SYSTEM AND METHOD OF RECOVERING SAID HEAT
GB2136880A (en) * 1983-03-18 1984-09-26 Rolls Royce Anti-icing of gas turbine engine air intakes
FR2552816A1 (en) * 1983-10-03 1985-04-05 Nuovo Pignone Spa ANTI-ICING SYSTEM FOR A GAS TURBINE
GB2278643A (en) * 1993-06-03 1994-12-07 Snecma De-icing system for forward parts of a gas turbine engine
EP3647205A1 (en) * 2018-10-29 2020-05-06 Pratt & Whitney Canada Corp. Method and system for cooling an auxiliary power unit using aircraft fuel
RU2806133C1 (en) * 2023-04-11 2023-10-26 Российская Федерация, От Имени Которой Выступает Министерство Промышленности И Торговли Российской Федерации Air blower for aircraft air conditioning system

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2536842A1 (en) * 1982-11-29 1984-06-01 Gen Electric ENGINE LUBRICATING OIL HEAT RECOVERY SYSTEM AND METHOD OF RECOVERING SAID HEAT
GB2136880A (en) * 1983-03-18 1984-09-26 Rolls Royce Anti-icing of gas turbine engine air intakes
FR2552816A1 (en) * 1983-10-03 1985-04-05 Nuovo Pignone Spa ANTI-ICING SYSTEM FOR A GAS TURBINE
GB2147364A (en) * 1983-10-03 1985-05-09 Nuovo Pignone Spa Anti-icing system for a gas turbine
GB2278643A (en) * 1993-06-03 1994-12-07 Snecma De-icing system for forward parts of a gas turbine engine
FR2705996A1 (en) * 1993-06-03 1994-12-09 Snecma Defrosting system of the front parts of a turbomachine.
US5423174A (en) * 1993-06-03 1995-06-13 Societe National D'etude Et De Construction De Moteurs D'aviation (S.N.E.C.M.A.) Anti-icing system for a gas turbine engine
GB2278643B (en) * 1993-06-03 1997-01-08 Snecma De-icing system for forward parts of a turboshaft engine
EP3647205A1 (en) * 2018-10-29 2020-05-06 Pratt & Whitney Canada Corp. Method and system for cooling an auxiliary power unit using aircraft fuel
RU2806133C1 (en) * 2023-04-11 2023-10-26 Российская Федерация, От Имени Которой Выступает Министерство Промышленности И Торговли Российской Федерации Air blower for aircraft air conditioning system

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