RU2059852C1 - Pulse hypersonic ram-jet engine - Google Patents

Abstract

FIELD: aircraft engine engineering. SUBSTANCE: engine has inlet device with detonation chamber, nozzle, and system for supplying gas producer products. The engine is set in operation when the aircraft velocity is 3.4-4 Mach numbers. The gas producer products having a fuel excess are fed simultaneously with supplying supersonic air through the flow passageway of the inlet device to the detonation chamber. Axial supersonic air jet impacts the flat jet of gas producer products at the focus of the detonation chamber. As a result, a system of shock waves arises in which temperature, pressure is increased abruptly as well as a great amount of heat is released. This, in turn, results in detonation of the products in air environment. Since the combustion is a pulse combustion, the thrust depends on the working frequency of the processes inside the chamber. EFFECT: enhanced efficiency. 1 dwg

Description

 The invention relates to pulsating jet engines with a resonant combustion chamber, as well as to ramjet pulsating jet engines.

 Closest to the technical result of the invention is the engine according to the patent of Germany N 1476819, class. F 02 C 5/10, 1970.

 However, it does not provide acceleration of the aircraft to the required speeds.

 The objective of the invention is to increase the speed of the aircraft by improving the design and operation of the engine.

 The solution to this problem is to improve the traction characteristics of the engine due to the intensification of intra-chamber processes by creating detonation (supersonic, shock) combustion in a pulsating mode. In turn, this leads to an increase in engine thrust and, consequently, to an increase in aircraft speed.

 The problem is achieved by the fact that the inner surface of the gas supply channel is made in the form of at least one conical surface turning into a cylindrical one before entering the detonation chamber.

 The drawing shows a pulsating scramjet.

 It contains a detonation chamber 1 with a gas supply channel 2 and a coaxially outlet nozzle 3 mounted to form an annular gap between it and the end of the chamber, in communication with the gas supply products supply unit.

 The detonation chamber 1 is a semi-closed cavity, made in the output part of the nozzle 1, and is designed to organize the process of pulsed detonation combustion.

 The gas supply channel 2 is an input device and is designed to supply air to the detonation chamber 1 with hypersonic (supersonic) speed. Such a flow of air contributes to the creation of shock waves (shock waves) in the detonation chamber 1, which intensify the combustion process.

 This task is achieved in that the device is made in the form of a body of revolution with a flow channel, the input part of which is formed by one or more slightly conical surfaces with half-open angles α and β turning into a cylindrical surface of diameter d. The output of the device is part of a semi-enclosed cavity forming a detonation chamber. The half-angle angles α and β are selected from the conditions for creating the necessary degree of deceleration of the air flow, which, in turn, is selected from the consideration of obtaining the maximum efficiency of the working process.

 In this case, the flow should not be inhibited to M ≅ 1.

 The outlet nozzles 3 are designed to increase the flow rate of detonation products, and therefore to create an additional component of the traction force and is a hollow body of revolution with a profiled inner surface.

 The node for supplying gas generation products 4 is intended for supplying products of incomplete combustion from the gas generator through an annular gap formed between the end face of the detonation chamber and the outlet nozzle into the internal volume of the chamber.

 The pulsating scramjet engine is put into operation after the aircraft has gained flight speed in the range of numbers M 3.5-4. At the same time, air is introduced into the detonation chamber 1 through the gas-dynamic channel and through the annular gap gas generation products with excess fuel. The collision of an axial supersonic air jet with a flat jet of gas generation products occurs in the geometric focus of the detonation chamber 1. At the same time, the volume of the detonation chamber 1, formed by its inner surface and a flat jet of gas generation products forming a gas-dynamic shutter, is filled.

 In the process of their collision, a system of shock waves (shock waves) arises, i.e., a sharp increase in temperature, pressure of detonation products and the release of a large amount of heat occur. In turn, this leads to detonation combustion of gas generation products in air. Detonation waves, propagating in a gaseous medium from the focus of detonation chamber 1, interact with its walls normal to the surface and, ricochet from it, pierce a flat stream of gas generation products and accelerate the movement of most of them towards the nozzle 3.

 In this case, the main component of the thrust force is created due to the interaction of detonation waves with the inner surface of the detonation chamber 1, and its additional component due to the acceleration of the movement of detonation products in the nozzle 3. Thus, as a result of the implementation of the above process, a thrust impulse appears, at the end of which again occurs the closure of a flat jet of gas generation products, and the process is repeated again with a frequency determined by the volume of the detonation chamber and the total second mass flow house air and gas generation products.

Claims (1)

 A PULSATING HYPERSONIC DIRECT-AIR AIR-REACTIVE ENGINE, comprising a detonation chamber with a gas supply channel and a coaxial exhaust nozzle installed to form an annular gap between it and the chamber end, connected to the gas supply products supply unit, wherein the surface is lesser than one in that a conical surface turning into a cylindrical one before entering the chamber.

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