DE1199626B - Device in an aircraft to prevent hot gases from a lift engine from being sucked into the inlet of a cruise engine - Google Patents
Device in an aircraft to prevent hot gases from a lift engine from being sucked into the inlet of a cruise engineInfo
- Publication number
- DE1199626B DE1199626B DEM56136A DEM0056136A DE1199626B DE 1199626 B DE1199626 B DE 1199626B DE M56136 A DEM56136 A DE M56136A DE M0056136 A DEM0056136 A DE M0056136A DE 1199626 B DE1199626 B DE 1199626B
- Authority
- DE
- Germany
- Prior art keywords
- engine
- cruise
- inlet
- aircraft
- sucked
- 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
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0041—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors
Description
Einrichtung bei einem Flugzeug zur Verhinderung des Ansaugens heißer Gase eines Hubtriebwerks in den Einlauf eines Marschtriebwerks Die Erfindung betrifft eine Einrichtung zur Verhinderung von Heißgasrezirkulation an Triebwerkseinläufen bei senkrecht startenden und landenden Luftfahrzeugen mit mindestens einem Marschtriebwerk mit seitlichen Lufteinläufen und mindestens einem Hubtriebwerk.Device in an aircraft to prevent hot water from being drawn in Gases of a lift engine in the inlet of a cruise engine The invention relates to a device to prevent hot gas recirculation at engine intakes in the case of aircraft taking off and landing vertically with at least one cruise engine with side air inlets and at least one lifting mechanism.
Derartige Triebwerkssysteme weisen den Nachteil auf, daß insbesondere beim Start durch die heißen Triebwerksabgase der Hubtriebwerke erwärmte Luft vom Marschtriebwerk angesaugt wird, wodurch eine Verminderung des Schubes eintritt.Such engine systems have the disadvantage that in particular when starting, the hot engine exhaust gases from the lift engines heat the air from the Cruise engine is sucked in, whereby a reduction in thrust occurs.
Die Erfindung behebt diesen Nachteil durch Ausblasen von Luft an den Einlauflippen der Marschtriebwerke entgegen der Anströmrichtung der heißen Gase, wodurch das Ansaugen derselben verhindert wird.The invention overcomes this disadvantage by blowing air to the Inlet lips of the cruise engines against the direction of flow of the hot gases, thereby preventing the same from being sucked in.
Die Figuren zeigen eine beispielsweise Ausführung der Erfindung, und zwar zeigt F i g. 1 eine Seitenansicht eines Flugzeuges mit Ausblasevorrichtung, F i g. 2 einen Triebwerkseinlauf mit Ausblaseeinrichtung.The figures show an exemplary embodiment of the invention, and although FIG. 1 shows a side view of an aircraft with a blow-out device, F i g. 2 an engine intake with a blow-out device.
Die F i g. 1 zeigt ein senkrecht startendes und landendes Luftfahrzeug 1 mit einem Marschtriebwerk 2 mit seitlichen Lufteinläufen 3 und einem fest eingebauten Hubtriebwerk 4. Das fest eingebaute Hubtriebwerk 4 besitzt eine fest angeordnete Strahldüse 5, während das Marschtriebwerk 2 eine verschwenkbare Austrittsdüse 6 besitzt, durch welche der Gasstrahl sowohl in horizontaler als auch in vertikaler Richtung abgelenkt werden kann. Die Verkleidung des Triebwerkseinlaufs 3 weist eine Kammer 7 auf, welche durch Düsen 8 (F i g. 2) mit der äußeren Atmosphäre in Verbindung steht. Die Kammer 7 steht ferner über eine Luftleitung 9 mit dem Verdichter des Marschtriebwerks 2 oder einem anderen Preßluftaggregat in Verbindung.The F i g. 1 shows an aircraft taking off and landing vertically 1 with a marching engine 2 with side air inlets 3 and a permanently installed one Lifting engine 4. The permanently installed lifting mechanism 4 has a fixed one Jet nozzle 5, while the cruise engine 2 has a pivotable outlet nozzle 6 possesses, through which the gas jet in both horizontal and vertical Direction can be deflected. The fairing of the engine intake 3 has a Chamber 7, which through nozzles 8 (Fig. 2) with the outside atmosphere in connection stands. The chamber 7 is also connected to the compressor of the via an air line 9 March engine 2 or another compressed air unit in connection.
Die durch die Strahldüsen 5 und 6 in vertikaler Richtung ausgestoßenen Heißgasstrahlen H haben bekanntlich das Bestreben, um den Triebwerkseinlauf 3 so zurückzuströmen, wie es durch die Pfeile Hl in F i g. 1 angedeutet ist. Durch die Luftleitung 9 wird beim Start- oder Landevorgang einem Verdichter entnommene Luft der Kammer 7 in der Nase des Triebwerkseinlaufs 3 zugeführt und durch die Düsen 8 (F i g. 2) nach außen geblasen, in der Weise, daß dadurch ein Luftschleier gebildet wird, welcher verhindert, daß die heißen, in F i g. 1 mit H1 bezeichneten Gase, welche die Nase des Triebwerkseinlaufs 3 umströmen, in den Triebwerkseinlauf eingesaugt werden.The ejected through the jet nozzles 5 and 6 in the vertical direction Hot gas jets H are known to strive to the engine inlet 3 so flow back, as indicated by the arrows Hl in FIG. 1 is indicated. Through the Air line 9 is air extracted from a compressor during takeoff or landing the chamber 7 in the nose of the engine inlet 3 and fed through the nozzles 8 (Fig. 2) blown outwards in such a way that an air curtain is thereby formed which prevents the hot ones shown in FIG. 1 gases labeled H1, which flow around the nose of the engine inlet 3, sucked into the engine inlet will.
Claims (2)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DEM56136A DE1199626B (en) | 1963-03-15 | 1963-03-15 | Device in an aircraft to prevent hot gases from a lift engine from being sucked into the inlet of a cruise engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DEM56136A DE1199626B (en) | 1963-03-15 | 1963-03-15 | Device in an aircraft to prevent hot gases from a lift engine from being sucked into the inlet of a cruise engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| DE1199626B true DE1199626B (en) | 1965-08-26 |
Family
ID=7308511
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| DEM56136A Pending DE1199626B (en) | 1963-03-15 | 1963-03-15 | Device in an aircraft to prevent hot gases from a lift engine from being sucked into the inlet of a cruise engine |
Country Status (1)
| Country | Link |
|---|---|
| DE (1) | DE1199626B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3447764A (en) * | 1966-05-21 | 1969-06-03 | Bristol Siddeley Engines Ltd | Aircraft with jet propulsion engine |
| DE1922351B1 (en) * | 1969-05-02 | 1971-02-18 | Dornier Ag | Airplane with jet engines for lift generation |
-
1963
- 1963-03-15 DE DEM56136A patent/DE1199626B/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3447764A (en) * | 1966-05-21 | 1969-06-03 | Bristol Siddeley Engines Ltd | Aircraft with jet propulsion engine |
| DE1922351B1 (en) * | 1969-05-02 | 1971-02-18 | Dornier Ag | Airplane with jet engines for lift generation |
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