RU97108163A - OIL COOLING EJECTOR SYSTEM FOR AUXILIARY AIRCRAFT ENGINE - Google Patents

OIL COOLING EJECTOR SYSTEM FOR AUXILIARY AIRCRAFT ENGINE

Info

Publication number
RU97108163A
RU97108163A RU97108163/28A RU97108163A RU97108163A RU 97108163 A RU97108163 A RU 97108163A RU 97108163/28 A RU97108163/28 A RU 97108163/28A RU 97108163 A RU97108163 A RU 97108163A RU 97108163 A RU97108163 A RU 97108163A
Authority
RU
Russia
Prior art keywords
aircraft
air
mounting compartment
auxiliary
oil cooling
Prior art date
Application number
RU97108163/28A
Other languages
Russian (ru)
Other versions
RU2131380C1 (en
Inventor
Винтер Андреас
Хибель Фолькер
Корус Андреас
Original Assignee
Даймлер-Бенц Эйроспейс Эйрбас ГмбХ
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
Priority claimed from DE19619535A external-priority patent/DE19619535C1/en
Application filed by Даймлер-Бенц Эйроспейс Эйрбас ГмбХ filed Critical Даймлер-Бенц Эйроспейс Эйрбас ГмбХ
Publication of RU97108163A publication Critical patent/RU97108163A/en
Application granted granted Critical
Publication of RU2131380C1 publication Critical patent/RU2131380C1/en

Links

Claims (3)

1. Эжекторная система масляного охлаждения для вспомогательного авиационного двигателя, которая установлена в монтажном отсеке заостренной хвостовой части самолета, причем монтажный отсек имеет доступ через люк обслуживания, а струйный насос использует кинетическую энергию струи выхлопных газов вспомогательного двигателя для создания всасывающего потока для всасывания охлаждающего воздуха из монтажного отсека через масляный радиатор, отличающаяся тем, что в люке (15) обслуживания заподлицо с внешней обшивкой установлен воздухозаборник (4) для всасывания при наземной эксплуатации воздуха из окружающего самолет пространства в монтажный отсек (1) к масляному радиатору (10) и для затекания при полетной эксплуатации части обтекающего самолет воздуха и введения с возрастанием давления в монтажный отсек (1) таким образом, что в нем создается избыточное давление по сравнению с возникающим на выхлопном сопле (6) противодавлением.1. The ejector oil cooling system for the auxiliary aircraft engine, which is installed in the mounting compartment of the pointed tail section of the aircraft, the mounting compartment being accessed through the service hatch, and the jet pump uses the kinetic energy of the exhaust jet of the auxiliary engine to create an intake stream to draw in cooling air from mounting compartment through an oil cooler, characterized in that an air intake is installed flush with the outer skin in the service hatch (15) nick (4) for suction during ground operation of air from the space surrounding the aircraft into the mounting compartment (1) to the oil cooler (10) and for inflowing during flight operation of part of the air flowing around the aircraft and introducing pressure into the mounting compartment (1) with increasing pressure in such a way that overpressure is created in it in comparison with the backpressure arising on the exhaust nozzle (6). 2. Система по п. 1, отличающаяся тем, что воздухозаборник выполнен прямоугольной формы и в воздуховпускной зоне приведен в соответствие с конструкцией самолета. 2. The system according to claim 1, characterized in that the air intake is rectangular in shape and brought into line with the aircraft structure in the air inlet zone. 3. Система по п. 1 или 2, отличающаяся тем, что за воздуховпускным отверстием (14) установлен диффузор (16). 3. The system according to claim 1 or 2, characterized in that a diffuser (16) is installed behind the air inlet (14).
RU97108163A 1996-05-15 1997-05-14 Ejector-type oil cooling system for auxiliary aircraft engine RU2131380C1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19619535A DE19619535C1 (en) 1996-05-15 1996-05-15 Ejector oil cooling system for an aircraft auxiliary engine
DE19619535.7 1996-05-15

Publications (2)

Publication Number Publication Date
RU97108163A true RU97108163A (en) 1999-04-27
RU2131380C1 RU2131380C1 (en) 1999-06-10

Family

ID=7794356

Family Applications (1)

Application Number Title Priority Date Filing Date
RU97108163A RU2131380C1 (en) 1996-05-15 1997-05-14 Ejector-type oil cooling system for auxiliary aircraft engine

Country Status (4)

Country Link
EP (1) EP0807576B1 (en)
DE (2) DE19619535C1 (en)
ES (1) ES2180839T3 (en)
RU (1) RU2131380C1 (en)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6092360A (en) * 1998-07-01 2000-07-25 The Boeing Company Auxiliary power unit passive cooling system
US6615576B2 (en) * 2001-03-29 2003-09-09 Honeywell International Inc. Tortuous path quiet exhaust eductor system
US6651929B2 (en) 2001-10-29 2003-11-25 Pratt & Whitney Canada Corp. Passive cooling system for auxiliary power unit installation
US20060163425A1 (en) * 2005-01-27 2006-07-27 Honeywell International, Inc. Aircraft inlet assembly for reducing auxiliary power unit noise
DE102007061588B4 (en) 2007-12-20 2011-07-21 Airbus Operations GmbH, 21129 Aircraft cooling system
US8444083B2 (en) 2011-06-30 2013-05-21 Hamilton Sundstrand Corporation Auxiliary power unit inlet
FR2986275B1 (en) * 2012-02-01 2016-07-01 Turbomeca GAS TURBINE EXHAUST GAS EJECTION METHOD AND OPTIMIZED CONFIGURATION EXHAUST ASSEMBLY
CN102673793B (en) * 2012-06-08 2015-04-29 中国航空工业集团公司西安飞机设计研究所 Exhaust ejector system of airplane auxiliary power unit
RU2587733C1 (en) * 2015-01-13 2016-06-20 Открытое акционерное общество "Научно-производственное предприятие "Аэросила" Ejector oil cooling system in power plant
RU2632561C2 (en) * 2016-02-15 2017-10-05 Владимир Леонидович Письменный Air-to-air radiator and method for efficiency increase
RU2696521C1 (en) * 2018-05-17 2019-08-02 Общество с ограниченной ответственностью "Газпром трансгаз Ухта" Method of reducing air temperature in cavity between conical housing of power turbine of engine al-31stn and internal housing of volute of gas transfer unit c1-16l/76-1.44
WO2023002132A1 (en) * 2021-07-21 2023-01-26 Flying Whales System for the thermal management of an external electric-power-generating nacelle equipping an electrically powered airship, nacelle and airship equipped with said system

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1803156A (en) * 1930-03-24 1931-04-28 Wagner Rudolf Air-cooled condenser for steam-driven vehicles
DE733564C (en) * 1938-03-17 1943-03-29 Ettore Bugatti Radiator arrangement on aircraft
GB723406A (en) * 1952-12-29 1955-02-09 Northrop Aircraft Inc Improvements in or relating to aircraft jet engine cooling system
US4504030A (en) * 1982-12-06 1985-03-12 United Technologies Corporation Cooling means
US5265408A (en) * 1992-02-13 1993-11-30 Allied-Signal Inc. Exhaust eductor cooling system
US5655359A (en) * 1995-05-15 1997-08-12 The Boeing Company Passive cooling device and method for cooling an auxiliary power unit on an airplane

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