DE1161765B - Arrangement of jet engines in the end of the fuselage of an aircraft - Google Patents

Arrangement of jet engines in the end of the fuselage of an aircraft

Info

Publication number
DE1161765B
DE1161765B DEM49924A DEM0049924A DE1161765B DE 1161765 B DE1161765 B DE 1161765B DE M49924 A DEM49924 A DE M49924A DE M0049924 A DEM0049924 A DE M0049924A DE 1161765 B DE1161765 B DE 1161765B
Authority
DE
Germany
Prior art keywords
fuselage
arrangement
aircraft
jacketed propeller
air
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.)
Pending
Application number
DEM49924A
Other languages
German (de)
Inventor
Dr-Ing Willy Messerschmitt
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.)
Messerschmitt AG
Original Assignee
Messerschmitt 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 AG filed Critical Messerschmitt AG
Priority to DEM49924A priority Critical patent/DE1161765B/en
Publication of DE1161765B publication Critical patent/DE1161765B/en
Pending legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
    • B64D27/02—Aircraft characterised by the type or position of power plant
    • B64D27/16—Aircraft characterised by the type or position of power plant of jet type
    • B64D27/20—Aircraft characterised by the type or position of power plant of jet type within or attached to fuselage

Description

Anordnung von Strahltriebwerken im Rumpfende eines Flugzeuges Die Erfindung bezieht sich auf ein Flugzeug mit einem luftatmenden Strahltriebwerksaggregat im Rumpfheck, wobei zwischen den an der Umfläche des Rumpfendes angeordneten Lufteinläufen und dem Triebwerksaggregat einerseits und dem Rumpfheck andererseits ,ein Kanal mit ringförmigem Querschnitt gebildet ist, durch den unter Mithilfe einer Mantelluftschraube die Grenzschicht des Rumpfes abgesaugt wird, nach Patent 11 46 761.Arrangement of jet engines in the end of the fuselage of an aircraft The invention relates to an aircraft with an air-breathing jet engine unit in the fuselage tail, with a channel with an annular cross-section being formed between the air inlets arranged on the surface of the fuselage end and the engine unit on the one hand and the fuselage tail on the other With the help of a jacketed propeller, the boundary layer of the fuselage is sucked off, according to patent 11 46 761.

In einer vorzugsweisen Anordnung nach Patent 1 146 761 treiben die Strahltriebwerke die Mantelluftschraube durch Anblasen von an den Enden der Mantelluftschraube angeordneten Turbinenschaufeln an.In a preferred arrangement according to patent 1,146,761, the drive Jet engines hit the jacketed propeller by blowing on the ends of the jacketed propeller arranged turbine blades.

Dabei zeigt sich, daß der Druck p1 hinter den Turbinenschaufeln etwa so groß wieder Druck p. hinter der Mantelluftschraube wird. Die Leistung der TL-Triebwerke kann daher über die Gasturbine nicht ganz ausgenutzt werden, da eine Expansion bis auf den Außendruck nicht möglich ist, weil der Druck p, hinter der Mantelluftschraube größer sein muß als der Außendruck.It can be seen that the pressure p1 behind the turbine blades is approximately so great again pressure p. behind the jacketed propeller. The performance of the TL engines can therefore not be fully utilized via the gas turbine, since an expansion up to on the external pressure is not possible because the pressure p, behind the jacketed propeller must be greater than the external pressure.

Die Erfindung behebt den Nachteil des Rückstaues aus p2 auf die Turbinenschaufeln durch eine besondere Abführung für die durch die Mantelluftschraube durchgesetzte Luft.The invention eliminates the disadvantage of the backwater from p2 on the turbine blades by a special discharge for the one enforced by the jacketed propeller Air.

Die Zeichnung zeigt eine beispielsweise Ausführung des Erfindungsgegenstandes.The drawing shows an example of an embodiment of the subject matter of the invention.

Die Anordnung der Triebwerke 4 und der Mantelluftschraube 1 ergibt eine Triebwerksanlage mit zwei Kreisen, wobei die Luft, welche durch die Mantelluftschraube 1 durchgesetzt wird und den zweiten Kreis bildet, durch ein besonderes Mantelrohr 5 a nach hinten abgeführt wird. Zur Abführung des Gasstrahles der Triebwerke ist .eine möglichst kurze ringförmige Gasstrahlaustrittsdüse 7 rings um die Turbinenschaufeln 2 und über diese herausragend angeordnet. Durch diese Anordnung ist es möglich, den Rückstau aus p, auf die Turbinenschaufeln in kleinsten Grenzen zu halten und dadurch die Leistung der TL-Triebwerke über die Gasturbine in weit höherem Maße auszunutzen.The arrangement of the engines 4 and the jacketed propeller 1 results in an engine system with two circles, the air which is passed through the jacketed propeller 1 and forms the second circle, is discharged through a special jacket tube 5 a to the rear. To discharge the gas jet from the engines, an annular gas jet outlet nozzle 7 which is as short as possible is arranged around the turbine blades 2 and protruding above them. This arrangement makes it possible to keep the backflow from p on the turbine blades within the smallest limits and thereby to utilize the power of the TL engines via the gas turbine to a far greater extent.

Claims (1)

Patentanspruch: Flugzeug mit einem luftatmenden Strahltriebwerksaggregat im Rumpfheck, wobei zwischen den an der Umfläche des Rumpfendes angeordneten Lufteinläufen und dem Triebwerksaggregat einerseits und dem Rumpfheck andererseits ein Kanal mit ringförmigem Querschnitt gebildet ist, durch den unter Mithilfe einer Mantelluftschraube die Grenzschicht des Rumpfes abgesaugt wird, nach Patent 1146761, dadurch g e k e n n -z e i c h n e t, daß der Luftstrom der Mantelluftschraube (1) in ein Mantelrohr (5a) von gleichem Durchmesser wie die Mantelluftschraube mündet, welches von einer wesentlich kürzeren ringförmigen Gasstrahlaustrittsdüse (7) des Triebwerksaggregates, (4) umgeben ist.Claim: Airplane with an air-breathing jet engine unit in the fuselage rear, whereby a channel with an annular cross-section through which the boundary layer of the fuselage is sucked off with the help of a jacketed propeller is formed between the air inlets arranged on the surface of the fuselage end and the engine unit on the one hand and the fuselage tail on the other hand Patent 1146761, characterized in that the air flow of the jacketed propeller (1) opens into a jacket tube (5a) of the same diameter as the jacketed propeller, which is surrounded by a much shorter annular gas jet outlet nozzle (7) of the engine assembly (4).
DEM49924A 1961-08-04 1961-08-04 Arrangement of jet engines in the end of the fuselage of an aircraft Pending DE1161765B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DEM49924A DE1161765B (en) 1961-08-04 1961-08-04 Arrangement of jet engines in the end of the fuselage of an aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DEM49924A DE1161765B (en) 1961-08-04 1961-08-04 Arrangement of jet engines in the end of the fuselage of an aircraft

Publications (1)

Publication Number Publication Date
DE1161765B true DE1161765B (en) 1964-01-23

Family

ID=7306677

Family Applications (1)

Application Number Title Priority Date Filing Date
DEM49924A Pending DE1161765B (en) 1961-08-04 1961-08-04 Arrangement of jet engines in the end of the fuselage of an aircraft

Country Status (1)

Country Link
DE (1) DE1161765B (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1294222B (en) * 1964-04-23 1969-04-30 Bristol Siddeley Engines Ltd Vertical take off and landing aircraft
EP3048048A1 (en) * 2015-01-21 2016-07-27 Rolls-Royce plc An aircraft

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1294222B (en) * 1964-04-23 1969-04-30 Bristol Siddeley Engines Ltd Vertical take off and landing aircraft
EP3048048A1 (en) * 2015-01-21 2016-07-27 Rolls-Royce plc An aircraft
US9815559B2 (en) 2015-01-21 2017-11-14 Rolls-Royce Plc Aircraft
US9994330B2 (en) 2015-01-21 2018-06-12 Rolls-Royce Plc Aircraft

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