DE950972C - Hot jet engine for propelling aircraft - Google Patents

Hot jet engine for propelling aircraft

Info

Publication number
DE950972C
DE950972C DEJ5394D DEJ0005394D DE950972C DE 950972 C DE950972 C DE 950972C DE J5394 D DEJ5394 D DE J5394D DE J0005394 D DEJ0005394 D DE J0005394D DE 950972 C DE950972 C DE 950972C
Authority
DE
Germany
Prior art keywords
hot jet
jet engine
compressor
engines
aircraft
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
DEJ5394D
Other languages
German (de)
Inventor
Dr-Ing Heinz Schmitt
Dipl-Ing Wolfgang Stein
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
Priority to DEJ5394D priority Critical patent/DE950972C/en
Application granted granted Critical
Publication of DE950972C publication Critical patent/DE950972C/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, 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
    • F02C7/26—Starting; Ignition
    • F02C7/262—Restarting after flame-out

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)

Description

Heißstrahltriebwerk zum Vortrieb von Luftfahrzeugen Die Erfindung betrifft Heißstrahltriebwerke zum Vortrieb von Luftfahrzeugen, bestehend aus einem Verdichter, einer Brennkammer oder deren mehreren und einer den Verdichter antreibenden Gasturbine mit anschließender Rückstoßdüse.Hot jet engine for propulsion of aircraft The invention relates to hot jet engines for propulsion of aircraft, consisting of a Compressor, a combustion chamber or several and one driving the compressor Gas turbine with adjoining thrust nozzle.

Es liegt im Wesen der Triebwerke der genannten Art, daß ihre Kraftstoffverbräuche bei geringen Leistungen oder im Leerlauf gegenüber dem Kraftstoffverbrauch bei Volleistung unverhältnismäßig hoch sind. Aus diesem Grunde müssen bei Flugzeugen, die mit mehreren derartigen Heißstrahltriebwerken ausgerüstet sind, im Reiseflug einige der Triebwerke außer Betrieb gesetzt werden, während die übrigen mit Vollast laufen.It is in the nature of the engines of the type mentioned that their fuel consumption at low power or when idling compared to fuel consumption at full power are disproportionately high. For this reason, aircraft with several such hot jet engines are equipped, some of the engines in cruise flight put out of operation while the others are running at full load.

Der Versuch, die zeitweilig abgeschaltet gewesenen Heißstrahltriebwerke während des Fluges wieder anzulassen, bereitet Schwierigkeiten: durch den Fahrtwind werden nämlich die abgestellten Triebwerke dauernd mit einer gewissen Drehzahl durchgedreht, und es tritt infolge der verhältnismäßig großen - durchgesetzten Luftmengen eine starke Abkühlung der abgestellten Triebwerke ein, durch welche das Wiederanfachen des Verbrennungsvorganges @in den Brennkammern wesentlich erschwert wird. Mit zunehmender Flughöhe werden diese nachteiligen Verhältnisse in steigendem Maße wirksam, was insbesondere deshalb ins Gewicht fällt, weil Luftfahrzeuge, die mit derartigen Triebwerken ausgerüstet sind, von vornherein für Flüge in großen Höhen bestimmt sind.The attempt to remove the hot jet engines that were temporarily switched off Starting again during the flight causes difficulties: due to the airstream namely, the shutdown engines are constantly cranked at a certain speed, and it occurs as a result of the comparatively large amounts of air that have passed through strong cooling of the shutdown engines, through which that Renewing the combustion process in the combustion chambers is made much more difficult will. With increasing flight altitude, these disadvantageous conditions increase Measures effective, which is particularly important because aircraft that are equipped with such engines, from the outset for flights in large Heights are determined.

Die Erfindung besteht in der Anordnung von Mitteln zum Festbremsen der umlaufenden Teile (z. B. Läufer des Verdichters oder Läufer der Gasturbine) des Triebwerkes. Durch das Festbremsen der Läufer der zeitweilig abgestellten Triebwerke wird der Durchsatz des Fahrtwindes durch diese wesentlich vermindert, ihre zu starke Abkühlung vermieden und ihr Wiederanlassen im Fluge erleichtert.The invention consists in the arrangement of means for locking the rotating parts (e.g. rotor of the compressor or rotor of the gas turbine) of the engine. By locking the rotors of the temporarily shut off engines the throughput of the airstream is significantly reduced by this, their too strong Avoid cooling and making it easier to restart in flight.

Die Bremsvorrichtung kann in irgendeiner bekannten Weise ausgebildet sein.The braking device can be constructed in any known manner be.

Claims (3)

PATENTANSPRÜCHE: i. Heißstrahltriebwerk zum Vortrieb von Luftfahrzeugen, bestehend aus einem Verdichter, einer Brennkammer oder deren mehreren und einer den Verdichter antreibenden Gasturbine mit anschließender Rückstoßdüse, gekennzeichnet durch Mittel zum Festbremsen der umlaufenden Teile des Triebwerkes zum Zwecke der Erleichterung des Anlassens im Fluge zeitweilig abgestellter Triebwerke. PATENT CLAIMS: i. Hot jet engine for propulsion of aircraft, consisting of a compressor, a combustion chamber or several and one the gas turbine driving the compressor with an adjoining recoil nozzle by means of braking the rotating parts of the engine for the purpose of Facilitating the starting of engines that are temporarily shut down in flight. 2. Heißstrahltriebwerk nach Anspruch i, dadurch gekennzeichnet, daß die Bremsvorrichtung an dem Läufer des Verdichters angeordnet ist. 2. Hot jet engine according to claim i, characterized in that the braking device is on the rotor of the compressor is arranged. 3. Heißstrahltriebwerk nach Anspruch i, dadurch gekennzeichnet, daß die Bremsvorrichtung an dem Läufer der Gasturbine angeordnet ist.3. hot jet engine according to claim i, characterized characterized in that the braking device is arranged on the rotor of the gas turbine is.
DEJ5394D 1943-04-30 1943-04-30 Hot jet engine for propelling aircraft Expired DE950972C (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DEJ5394D DE950972C (en) 1943-04-30 1943-04-30 Hot jet engine for propelling aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DEJ5394D DE950972C (en) 1943-04-30 1943-04-30 Hot jet engine for propelling aircraft

Publications (1)

Publication Number Publication Date
DE950972C true DE950972C (en) 1956-10-18

Family

ID=7198369

Family Applications (1)

Application Number Title Priority Date Filing Date
DEJ5394D Expired DE950972C (en) 1943-04-30 1943-04-30 Hot jet engine for propelling aircraft

Country Status (1)

Country Link
DE (1) DE950972C (en)

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