Propelling nozzle

Details Propelling nozzle Propelling nozzle

1991-09-19

1993-02-16

Kashnikow, Andres

Fluid sprinkling, spraying, and diffusing

Reaction motor discharge nozzle

With means controlling amount, shape or direction of...

23926535, 60230, 602701, 60271, 244125, 244 73R, F02K 112, F02K 310, F02K 978, B64D 2716

Patent

active

051863901

DESCRIPTION:

BRIEF SUMMARY
BACKGROUND AND SUMMARY OF THE INVENTION

The invention relates to a propelling nozzle and, more particularly, to a propelling nozzle having a variable course of the nozzle contour for flight aggregates operated in the subsonic, supersonic and hypersonic range.
The nozzle has upper and lower primary and secondary flaps which are disposed opposite one another at a mutual distance and which are sealingly movably guided between lateral wall portions of a four-cornered nozzle housing. The primary flaps are arranged pivotally about a fixed axis of rotation on the nozzle housing. The secondary flaps, in each case upstream of levers non-rotatably connected with the primary flaps, are pivotally linked to pivots situated on the side facing away from the nozzle flow. The secondary flaps change into the primary flaps with a surface section which is bent concentrically with respect to the pivots. The propelling nozzle is arranged between the jet pipe of a turboramjet engine and a radially exterior expansion ramp of the flight aggregate.
Recently, combined turboramjet engines, among others, have regained importance, specifically within the scope of so-called "hypersonic flight concepts" having a extremely high spectrum of application from the start to the high supersonic speed at high flight altitudes, e.g. up to an altitude of approximately 30 km. In this case the "hypersonic flight concepts" includes among other things a space flight aggregate concept, i.e. the "Sanger" Project which amounts to a two-stage concept, as described in the following. The first stage is to be carried out by a flight aggregate operating only within the atmosphere, while the second stage is based on a useful-load flight aggregate which is taken along "piggyback" by the mentioned flight aggregate and which, for the purpose of space mission, in the upper range of the atmosphere, by means of a suitable rocket propulsion system, is to independently continue on the flight path assigned to it. The flight aggregate responsible for the first stage can therefore return and be reused. The flight aggregate carries out starts and landings like a conventional airplane.
In the case of combined turboramjet engines which are to be used, for example, for a flight aggregate of this type, generally, when a flying speed of approximately Mach 3 is reached, the turbojet engine is to be switched off continuously, and the respective ramjet propulsion is to be switched on continuously. Thus, by means of the ramjet propulsion alone, desired high supersonic or hypersonic speeds are reached of up to Mach 4.5 or even more. Flying speeds of approximately Mach 2 or even more may be achieved in this case in the combined operation of "jet engine with a switched-on afterburner". The afterburner, which for this purpose is advantageously connected behind the jet engine part, is possibly acted upon by a combination of compressor or fan air and engine exhaust gas. The afterburner, by means of the connection of additional fuel injection devices together with flame stabilizers, may form the propulsion system for the ramjet operation, with a correspondingly proportioned exclusive ambient-air supply when the turbojet engine part is switched off.
In view of the above-mentioned extremely different flying, performance and ambient conditions, it is difficult to provide a propelling nozzle configuration by means of which essentially the following criteria must be brought into accord economically and optimally with respect to performance.
First, adaptation of the nozzle throat cross-section area (narrowest cross-section) to given, possibly extremely variable mass flows in the case of a flow Mach number (M.about.)=1 which can be adjusted in the plane of cross-section of the nozzle throat. This measure is necessary in the case of variable mass flows in order to always ensure the formation of a supersonic flow in the expansion part of the propelling nozzle.
Second, losses of flow energy or aerodynamic losses, as a result of the nozzle adjustment, must be kept low. The required variability of

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patent: 5094070 (1992-03-01), Enderle
Abstracts of New Technology (from the Air Force Systems Command); PB81-970485, 80-287, "2D/CD Nozzle with Cavity Pressure Control".

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