RU1800080C - Turbo-ramjet engine - Google Patents

Description

for example, a pneumatic shutdown mechanism connected by a conduit 16 through a regulating member 17 to an outlet cavity of the compressor 5. The additional combustion chamber 14 of the flow loop 2 is provided with control elements in the form of pivoting flaps 18 providing the required flow rate of the working fluid. Regulating elements in the form of pivoting valves 19 are placed in the flow path 2, which change the height of the shock wave front ..

Figure 2 shows a horizontal projection of the front of a shock wave. Section I of the front of the head shock wave is characterized as a section of the forward shock, sections 11.111 of the front of the head shock wave are characterized as sections of oblique jumps, where W is the velocity of the working fluid incident on the body that is not streamlined, and V is the velocity of the poorly streamlined body.

Works turboprop winding engine as follows.

The compressor 5 compresses the incoming air through an adjustable input device 3. In the combustion chamber 6, fuel is burned and the resulting combustion products, expanding in the turbine 7, rotate the compressor 5. At a low speed of incident air flow, the low pressure turbine 3 is blocked by the friction device 15. It is stationary. The high-temperature throto-turbocompressor circuit 1 ejects the flow of the flow-through circuit 2. With an increase in the speed of the incoming air flow, a signal is sent to the regulator 17, which opens the air from the compressor outlet 5 through the pipe 16 into the cavity of the pneumatic shutdown mechanism of the friction device 15, freeing from blocking low pressure turbine 8. It spins up to a predetermined speed. The fuel supply system 12 is turned on with an ignition device of the flow-through circuit 2, which makes it possible to prepare a combustible air-fuel mixture in the flow part and ignite it. Poorly streamlined bodies 13, at a low speed, rotate the flow, acting as flame stabilizers. Upon reaching a predetermined rotation frequency of the poorly flowed chambers 13, they form a shock wave front across the flow of the air-fuel mixture in the flow part of the flow path 2, in addition to the heat effect, on the mechanism of chemical reactions of the process. The mechanism of chain (spontaneous) self-acceleration of chemical reactions caused by

not only by the transmitted shock front, which changes the local parameters of temperature and pressure, but also of the reflected waves arising from the interaction of the traveling

shock wave with the outer surface of the flow part, where local zones of high pressures and temperatures are created between the reflected shock wave and the surface, as a result of which a high

degree of completeness of combustion. The flow of combustion products of both circuits are mixed and, expiring from the output device 4, create a jet stream.

With increasing speed.

air at high supersonic speeds, a signal is sent to close the regulator 17 to maintain pressure in the cavity of the pneumatic shutdown mechanism of the friction device 15. The fuel supply to the combustion chamber 6 is cut off. The high pressure turbine and compressor 5 rotate automatically. tional mode. An additional combustion chamber 1.4 operates, the combustion products of which, expanding in the low pressure turbine 8 and passing along the path of the additional crown of the blades 10, provide the required frequency of rotation of the free turbine 8 to form a shock wave front across the flow in the flow part of the engine flow path 2. The change in the rotation frequency of the turbine 8 is provided by changing the flow rate of the working fluid in the additional combustion chamber 14 using control elements in the form of rotary valves 18. By changing the position of the individual rotary valves 19, the concentration field of the combustion products in the flow part is uniform by changing the local turbulization of the molasses .

Claims (1)

SUMMARY OF THE INVENTION A turboprop engine comprising a turbocompressor circuit with high and low pressure turbines and a flow circuit with a fuel supply system and flame stabilizers made in the form of poorly streamlined bodies, characterized in that, in order to intensify the process of fuel combustion in flow modes work in a wide range of speeds of air entering the engine inlet, low turbine the pressure is equipped with an additional crown of blades mounted outside the crown of the working blades, and is made free, the flow-through circuit of the engine is equipped with an additional combustion chamber located at the inlet to the additional the crown of the blades, and poorly streamlined outside the additional crown of the blade are installed uniformly around the circumference. PuZ.1 A (increased) 9th. 2