FR2266806A1 - Series jet rocket engine has two pref parallel shafts - each with one turbine to give reduced shaft and engine length - Google Patents

Series jet rocket engine has two pref parallel shafts - each with one turbine to give reduced shaft and engine length

Info

Publication number
FR2266806A1
FR2266806A1 FR7508423A FR7508423A FR2266806A1 FR 2266806 A1 FR2266806 A1 FR 2266806A1 FR 7508423 A FR7508423 A FR 7508423A FR 7508423 A FR7508423 A FR 7508423A FR 2266806 A1 FR2266806 A1 FR 2266806A1
Authority
FR
France
Prior art keywords
series
turbine
combustion chamber
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.)
Granted
Application number
FR7508423A
Other languages
French (fr)
Other versions
FR2266806B1 (en
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.)
Airbus Defence and Space GmbH
Original Assignee
Messerschmitt Bolkow Blohm AG
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 Messerschmitt Bolkow Blohm AG filed Critical Messerschmitt Bolkow Blohm AG
Publication of FR2266806A1 publication Critical patent/FR2266806A1/en
Application granted granted Critical
Publication of FR2266806B1 publication Critical patent/FR2266806B1/fr
Granted 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
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44—Feeding propellants
    • F02K9/46—Feeding propellants using pumps
    • F02K9/48—Feeding propellants using pumps driven by a gas turbine fed by propellant combustion gases or fed by vaporized propellants or other gases

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A series jet engine for rocket propulsion has a pre-combustion chamber, two mechanically independent (H.P. and L.P.) turbines driving fuel pumps, a principal combustion chamber, and the jet nozzle, all arranged thermodynamically in series. Physically, the layout has two (parallel) principal axes (A,B) which comprise the following series of items, considered in succession from an imaginary plane (E) immediately downstream of the jet outlet, axis (A), pre-combustion chamber, H.P. turbine, (fuel) pump, axis (B), principal combustion chamber with jet nozzle, L.P. turbine (fuel) pump. Pref. the H.P. and L.P. turbines lie approximately opposite to each other. The features of a series jet engine, esp. continuing increase in specific thrust with increasing pressure, are obtained, without the disadvantage of a long shaft. The H.P. exhaust and the L.P. inlet are rotationally symmetrical chambers and are connected by a transverse tubular duct whose axis intersects the axes (A,B) pump is for liquid hydrogen, the second for liquid oxygen. The inlets, to the pumps are coaxial with the pumps.
FR7508423A 1974-04-05 1975-03-18 Series jet rocket engine has two pref parallel shafts - each with one turbine to give reduced shaft and engine length Granted FR2266806A1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19742416766 DE2416766C3 (en) 1974-04-05 1974-04-05 Main stream rocket engine

Publications (2)

Publication Number Publication Date
FR2266806A1 true FR2266806A1 (en) 1975-10-31
FR2266806B1 FR2266806B1 (en) 1978-12-29

Family

ID=5912297

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7508423A Granted FR2266806A1 (en) 1974-04-05 1975-03-18 Series jet rocket engine has two pref parallel shafts - each with one turbine to give reduced shaft and engine length

Country Status (4)

Country Link
JP (1) JPS5824616B2 (en)
DE (1) DE2416766C3 (en)
FR (1) FR2266806A1 (en)
IN (1) IN142773B (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3003904A1 (en) * 2013-03-29 2014-10-03 Snecma PROPULSION ENGINE WITH ANNULAR GAS GENERATOR

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6065879A (en) * 1983-09-22 1985-04-15 三洋電機株式会社 Automatic door closing apparatus
FR2921979B1 (en) * 2007-10-08 2014-06-13 Astrium Sas DEVICE AND METHOD FOR PUMP MOTORIZATION FOR INTERNAL COMBUSTION ENGINE FUSE ENGINE

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE977815C (en) * 1963-12-21 1970-12-03 Messerschmitt Boelkow Blohm Liquid rocket engine
DE1264870B (en) * 1965-10-21 1968-03-28 Boelkow Gmbh Liquid rocket engine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3003904A1 (en) * 2013-03-29 2014-10-03 Snecma PROPULSION ENGINE WITH ANNULAR GAS GENERATOR

Also Published As

Publication number Publication date
JPS5824616B2 (en) 1983-05-23
DE2416766C3 (en) 1978-05-24
FR2266806B1 (en) 1978-12-29
IN142773B (en) 1977-08-27
DE2416766A1 (en) 1975-10-16
JPS50136509A (en) 1975-10-29
DE2416766B2 (en) 1977-09-29

Similar Documents

Publication Publication Date Title
US3496725A (en) Rocket action turbofan engine
US2585626A (en) Turbine mechanism for driving the fuel pumps of rockets
US2411227A (en) Power plant for airplanes
GB749176A (en) Improvements relating to jet propulsion apparatus
GB749009A (en) An improved jet propulsion plant
US2689454A (en) Rocket engine
GB1413845A (en) Marine propulsion
US3812672A (en) Supercharged ejector ramjet aircraft engine
GB1230203A (en)
GB1069217A (en) Improvements relating to engines
US3040519A (en) Jet propulsion unit with cooling means for incoming air
US3672165A (en) Method of feeding liquid propellants to gas generators or rocket combustion chambers and feeding system for performing the method
US7762056B2 (en) Aircraft combination engines exhaust thrust recovery
US3396538A (en) Water injection for thrust augmentation
GB685944A (en) Improvements in jet propulsion engines
GB1213497A (en) Liquid fuelled rocket propulsion unit
FR2266806A1 (en) Series jet rocket engine has two pref parallel shafts - each with one turbine to give reduced shaft and engine length
JPS59557U (en) Mainstream structure type liquid fuel rocket drive engine
US2757509A (en) Jet reaction propulsion units utilizing a pressure exchanger
JPH06212996A (en) Aero-engine
GB1329803A (en) Gas generator and method of operation
GB1089055A (en) Combined combustion chamber and propulsive unit for a rocket engine
GB851153A (en) Gas turbine jet-propulsion engine of the by-pass type
JPH0672575B2 (en) Gas injection system for turbo-ram rocket coupled propulsion engine
US3312067A (en) Jet propulsion unit

Legal Events

Date Code Title Description
ST Notification of lapse