AU1135001A - Turbojet engine - Google Patents

Turbojet engine

Info

Publication number
AU1135001A
AU1135001A AU11350/01A AU1135001A AU1135001A AU 1135001 A AU1135001 A AU 1135001A AU 11350/01 A AU11350/01 A AU 11350/01A AU 1135001 A AU1135001 A AU 1135001A AU 1135001 A AU1135001 A AU 1135001A
Authority
AU
Australia
Prior art keywords
flow
channel
jet
turbojet engine
pref
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
AU11350/01A
Inventor
Mathias Meyer
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Publication of AU1135001A publication Critical patent/AU1135001A/en
Abandoned legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
    • F02K1/34—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow for attenuating noise
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/46—Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing
    • F02K1/48—Corrugated nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/077—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
    • 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
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The turbojet engine (1) has a double-tube structure with an inner flow channel (14) and an outer flow channel (12) shrouding it. The main flow (11) is passed into the outer channel (12) with an auxiliary flow (13) into the inner channel (14). The inner channel (14) is formed by a hollow shaft (10), open at both ends. The gap between the end of the inner flow channel (14) and the jet thrust plane (16) is pref. 10-25% of the jet diameter at the jet thrust plane. The auxiliary flow is 5-20% of the main jet mass flow, and pref. 5-10%.
AU11350/01A 1999-12-23 2000-10-10 Turbojet engine Abandoned AU1135001A (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19962617A DE19962617C2 (en) 1999-12-23 1999-12-23 Turbo jet engine
DE19962617 1999-12-23
PCT/EP2000/009889 WO2001048365A1 (en) 1999-12-23 2000-10-10 Turbojet engine

Publications (1)

Publication Number Publication Date
AU1135001A true AU1135001A (en) 2001-07-09

Family

ID=7934238

Family Applications (1)

Application Number Title Priority Date Filing Date
AU11350/01A Abandoned AU1135001A (en) 1999-12-23 2000-10-10 Turbojet engine

Country Status (5)

Country Link
EP (2) EP1240421B1 (en)
AT (1) ATE291164T1 (en)
AU (1) AU1135001A (en)
DE (2) DE19962617C2 (en)
WO (1) WO2001048365A1 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2405666A (en) * 2003-09-05 2005-03-09 Dunlop Aerospace Ltd Noise attenuator, eg for turbofan engine air bleed system
GB2447291A (en) * 2007-03-08 2008-09-10 John Edward Randell A turbojet engine having a bypass flow through the engine core
WO2009068048A1 (en) * 2007-11-27 2009-06-04 Schneiderbauer-Schwendler, Enno Drive device with compression modification in the form of a thermal rotary engine with internal combustion
CN108412615A (en) * 2018-04-25 2018-08-17 大连恒通和科技有限公司 Vortex-spraying type power generation combustor

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB706841A (en) * 1948-07-17 1954-04-07 Devendra Nath Sharma Improvements relating to turbine jet propulsion power units
GB737081A (en) * 1949-12-09 1955-09-21 Devendra Nath Sharma Improvements relating to jet propulsion engines
US2696078A (en) * 1952-08-30 1954-12-07 Waitzman Simon Jet propulsion apparatus having a combination ram-jet and turbojet engine
GB919113A (en) * 1960-03-11 1963-02-20 Alexander Davidson Garden Improvements in or relating to aircraft propulsive means
GB1134996A (en) * 1967-04-21 1968-11-27 Lev Iosifovich Sorkin Jet noise suppressor in jet engine
US3982696A (en) * 1975-07-01 1976-09-28 Grumman American Aviation Corporation Jet noise suppressor nozzle
FR2389772A1 (en) * 1977-05-05 1978-12-01 Mordellet Roger Jet engine for subsonic aircraft - has hollow rotor with internal blades to produce secondary stream of air within annular primary stream
US4291782A (en) * 1979-10-30 1981-09-29 The Boeing Company Simplified method and apparatus for hot-shield jet noise suppression
FR2605679B1 (en) * 1986-10-24 1991-11-15 Culica Georges Francois TURBO ROTOR TURBOREACTOR, MULTIPLE BODIES AND MULTIPLE FLOWS
US5092425A (en) * 1990-04-02 1992-03-03 The United States Of America As Represented By The Secretary Of The Air Force Jet noise suppressor and method
US5154052A (en) * 1990-05-07 1992-10-13 General Electric Company Exhaust assembly for a high speed civil transport aircraft engine
GB2289504B (en) * 1994-05-11 1998-01-14 British Aerospace Gas turbine propulsion unit

Also Published As

Publication number Publication date
WO2001048365A1 (en) 2001-07-05
DE19962617A1 (en) 2001-07-12
EP1240421B1 (en) 2005-03-16
EP1469184A1 (en) 2004-10-20
DE50009822D1 (en) 2005-04-21
EP1240421A1 (en) 2002-09-18
DE19962617C2 (en) 2001-10-11
ATE291164T1 (en) 2005-04-15

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Legal Events

Date Code Title Description
MK6 Application lapsed section 142(2)(f)/reg. 8.3(3) - pct applic. not entering national phase