DE4040860A1 - Jet engine for aircraft - has partition forming inner combustion chambers and outer free-jet chambers with Laval nozzles - Google Patents

Jet engine for aircraft - has partition forming inner combustion chambers and outer free-jet chambers with Laval nozzles

Info

Publication number
DE4040860A1
DE4040860A1 DE19904040860 DE4040860A DE4040860A1 DE 4040860 A1 DE4040860 A1 DE 4040860A1 DE 19904040860 DE19904040860 DE 19904040860 DE 4040860 A DE4040860 A DE 4040860A DE 4040860 A1 DE4040860 A1 DE 4040860A1
Authority
DE
Germany
Prior art keywords
jet
combustion chambers
chambers
engine
turbine
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.)
Ceased
Application number
DE19904040860
Other languages
German (de)
Inventor
Franz-Josef Weber
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
Priority to DE19904040860 priority Critical patent/DE4040860A1/en
Publication of DE4040860A1 publication Critical patent/DE4040860A1/en
Ceased 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
    • F02K9/74—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant
    • F02K9/78—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with an air-breathing jet-propulsion plant
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F02K7/16—Composite ram-jet/turbo-jet engines

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)
  • Supercharger (AREA)

Abstract

The jet engine comprises a turbine with additional high-temp. free-jet combustion chambers in the air bypass passage. It has a propulsion unit with a tail ring. The larger combustion chambers (1-1 - 1-4) are divided by a partition (1-2) parallel to the engine axis into inner combustion chambers (1-3) aimed towards the turbine (1-5), and outer free-jet combustion chambers (1-4). These have Laval nozzles (1-6) directly connected to them. USE/ADVANTAGE - The free-jet chambers also can be mounted immediately adjacent to the compressor outlet.

Description

Gegenstand der Erfindung ist eine als Motor für Mehrfach-Überschall- Flugzeuge dienende Triebswerks-Kombination aus einer Strahlturbine mit zusätzlichen in einem Bypass-Luftkanal angeordneten Freistrahl-Brennkammern, welche mit ihren unmittelbar angeschlossenen Lavaldüsen die ganze den Brennkammern zugeführte Wärmemenge des Brennstoffes während des Ausström-Vorganges in der Lavaldüse abbauen und dabei mit der größtmöglichen Brenngas-Geschwindigkeit Maximal-Schub erzeugen. Der innen mit Keramik ausgekleideten Freistrahl-Brennkammer kann eine für Maximal-Schub berechnete Maximal-Temperatur - wie bei Raketen-Triebwerken - zugemutet werden.The invention relates to a motor for multiple supersonic Aircraft-serving engine combination consisting of a jet turbine additional free-jet combustion chambers arranged in a bypass air duct, which with their directly connected Laval nozzles whole amount of heat of the fuel supplied to the combustion chambers during of the outflow process in the Laval nozzle and thereby generate maximum thrust with the highest possible fuel gas speed. The inside with Ceramic lined free jet combustion chamber can be used for maximum thrust calculated maximum temperature - as with rocket engines - expected will.

Ein derartiges Triebwerk ist mit der deutschen Offenlegungsschrift DE 38 03 876.5 A1 vom 15.09.88 bekanntgeworden, welches am Ende eines mit dem Verdichterstutzen in Verbindung stehenden Bypass-Luftkanals Hochtemperatur-Brennkammern mit unmittelbar angeschlossenen Lavaldüsen hat. Außerdem ist in Verlängerung des Bypass-Luftkanals ein Heck-Ring- Staustrahltriebwerk nachgeordnet, und ein auf der Triebwerksmitte vorgesehenes Raketentriebwerk vollendet die Antriebs-Möglichkeiten. - Den Triebwerks-Einlauf steuert ein Kegelstumpf-Drehschieber. Nachteilig wirkt sich im vorgenannten Triebwerk die sehr große Entfernung der ins Freie abblasenden Brennkammern zum Verdichterstutzen für ihren Wirkungsgrad aus.Such an engine is with the German published application DE 38 03 876.5 A1 from 15.09.88, which at the end of a bypass air duct connected to the compressor nozzle High temperature combustion chambers with directly connected Laval nozzles Has. In addition, an extension of the bypass air duct is a rear ring Downstream jet engine, and one provided in the middle of the engine Rocket engine completes the propulsion options. - A truncated cone rotary valve controls the engine inlet. The very long distance has a disadvantage in the aforementioned engine of the combustion chambers that blow off to the compressor nozzle for their efficiency.

Aufgabe dieser Erfindung war es daher, auch die Freistrahl-Brennkammern in nächste Nähe des Verdichterstutzens zu bringen. Die Lösung dieser Aufgabe ist im kennzeichnenden Teil des Patentanspruchs 1 angegeben.The object of this invention was therefore also the free jet combustion chambers in the immediate vicinity of the compressor nozzle. The solution to this problem is in the characterizing part of the claim 1 specified.

Die Abb. 1 stellt mit dem halben Längsschnitt das aus der Strahlturbine 1 und dem Heck-Ring-Staustrahltriebwerk bestehende Triebwerk dar, wobei die Stufenzahlen der Beschaufelungen nur symbolisch und nicht maßgeblich, abgebildet sind. - Erfindungsgemäß sind die größer ausgeführten und in Brennkammer-Gehäusen 1-1 angeordneten Brennkammern 1-1 bis 1-4 durch eine zur Triebwerksmitte parallele Trennwand 1-2 in innere, auf die Turbine 1-5 gerichtete Turbinen-Brennkammer 1-3 und äußere Freistrahl-Brennkammern 1-4 mit unmittelbar angeschlossenen Lavaldüsen 1-6 geteilt. Da für den Verdichter-Antrieb bekanntlich 2/3 der Turbi­ nen-Leistung erforderlich sind, soll die Brennstoff-Zuteilung zu den vorgenannten Turbinen-Brennkammern 1-3 mit 2/3 und zu den Freistrahl- Brennkammern 1-4 mit 1/3 der Gesamtmenge erfolgen. Fig. 1 shows with half the longitudinal section the engine consisting of the jet turbine 1 and the rear-ring ramjet engine, the number of stages of the blades being shown only symbolically and not significantly. - According to the invention, the larger combustion chambers 1-1 to 1-4 arranged in the combustion chamber housings 1-1 are separated by a partition wall 1-2 parallel to the center of the engine into the inner, toward the turbine 1-5 turbine combustion chamber 1-3 and outer Free jet combustion chambers 1-4 shared with directly connected Laval nozzles 1-6 . As is known, 2/3 of the turbine power is required for the compressor drive, the fuel allocation to the above-mentioned turbine combustion chambers 1-3 with 2/3 and to the free-jet combustion chambers 1-4 with 1/3 of the Total amount.

Die Abb. 2 stellt mit dem halben Querschnitt A-B die Brennkammern 1-1 bis 1-4 als sektorenförmige leicht herausnehmbare Einheiten dar, wobei deren Gehäuse-Wanddicken möglichst dünn sein sollen. Ihre Anzahl hängt ab vom Triebwerks-Durchmesser, ihrer Demontage-Möglichkeit und Zugänglichkeit zu den Brennstoff-Einspritzdüsen. Zum Verdichter-Aus­ trittsstutzen hin sind ihre Gehäuse-Wände zugespitzt. Fig. 2 shows half the cross-section AB of the combustion chambers 1-1 to 1-4 as sector-shaped, easily removable units, the housing wall thicknesses of which should be as thin as possible. Their number depends on the engine diameter, their disassembly options and access to the fuel injectors. The housing walls are pointed towards the compressor outlet.

Der mit dieser Technik erzielbare Fortschritt besteht in der Vergrößerung des Wirkungsgrades der Freistrahl-Brennkammern 1-4, was sich als Geschwindigkeits-Steigerung auswirkt.The progress that can be achieved with this technology is to increase the efficiency of the free-jet combustion chambers 1-4 , which has the effect of increasing the speed.

Die Anwendung dieses Triebwerkes empfiehlt sich nicht allein für Mehr­ fach-Überschall-Flugzeuge mittlerer Größe, sondern auch als Start-Motor für Satelliten-Transport, wenn ein separater Raketenmotor zugefügt ist.The use of this engine is not recommended for more alone fold supersonic aircraft of medium size, but also as a starting engine for satellite transport when a separate rocket motor is added.

Claims (1)

Strahltriebwerk, bestehend aus einer Strahlturbine mit zusätzlichen Hoch­ temperatur-Freistrahl-Brennkammern im Bypass-Luftkanal und einem Heck- Ring-Staustrahltriebwerk, dadurch gekennzeichnet, daß die größer ausgeführten Brennkammern (1-1) bis (1-4) durch eine zur Trieb­ werksmitte parallele Trennwand (1-2) in innere, auf die Turbine (1-5) gerichtete, Turbinen-Brennkammern (1-3) und äußere Freistrahl-Brennkammern (1-4) mit unmittelbar angeschlossenen Lavaldüsen (1-6) geteilt sind.Jet engine, consisting of a jet turbine with additional high-temperature free-jet combustion chambers in the bypass air duct and a rear-ring ramjet engine, characterized in that the larger combustion chambers ( 1-1 ) to ( 1-4 ) by one to the center of the engine parallel partition ( 1-2 ) are divided into inner, directed towards the turbine ( 1-5 ), turbine combustion chambers ( 1-3 ) and outer free jet combustion chambers ( 1-4 ) with directly connected Laval nozzles ( 1-6 ).
DE19904040860 1990-12-20 1990-12-20 Jet engine for aircraft - has partition forming inner combustion chambers and outer free-jet chambers with Laval nozzles Ceased DE4040860A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE19904040860 DE4040860A1 (en) 1990-12-20 1990-12-20 Jet engine for aircraft - has partition forming inner combustion chambers and outer free-jet chambers with Laval nozzles

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19904040860 DE4040860A1 (en) 1990-12-20 1990-12-20 Jet engine for aircraft - has partition forming inner combustion chambers and outer free-jet chambers with Laval nozzles

Publications (1)

Publication Number Publication Date
DE4040860A1 true DE4040860A1 (en) 1991-08-29

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008076318A2 (en) 2006-12-18 2008-06-26 Aerojet-General Corporation Combined cycle integrated combustor and nozzle system

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3677012A (en) * 1962-05-31 1972-07-18 Gen Electric Composite cycle turbomachinery
DE3803876A1 (en) * 1988-02-09 1988-09-15 Weber Franz Josef Jet engine combination

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3677012A (en) * 1962-05-31 1972-07-18 Gen Electric Composite cycle turbomachinery
DE3803876A1 (en) * 1988-02-09 1988-09-15 Weber Franz Josef Jet engine combination

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008076318A2 (en) 2006-12-18 2008-06-26 Aerojet-General Corporation Combined cycle integrated combustor and nozzle system
EP2094963A2 (en) * 2006-12-18 2009-09-02 Aerojet-General Corporation Combined cycle integrated combustor and nozzle system
EP2094963A4 (en) * 2006-12-18 2011-08-03 Aerojet General Co Combined cycle integrated combustor and nozzle system
US8701379B2 (en) 2006-12-18 2014-04-22 Aerojet-General Corporation Combined cycle integrated combustor and nozzle system

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Legal Events

Date Code Title Description
OAV Applicant agreed to the publication of the unexamined application as to paragraph 31 lit. 2 z1
8120 Willingness to grant licenses paragraph 23
8110 Request for examination paragraph 44
8131 Rejection