RU2608426C2 - Versatile air-breather engine - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: air-breather engine comprises housing with air intake, compressor with outlet straightener, gas turbine engine, jet nozzle. After gas turbine engine combustion chamber is arranged with arranged along engine housing circumference prior to its input controlled external and internal shutoff shutters.

EFFECT: invention is aimed at creation of air-breather engine with low weight and dimensions, reduced air drag and fuel consumption, and extended service life.

1 cl, 1 dwg

Description

The invention relates to an jet engine, is intended to achieve high speeds and heights by an air vessel using a universal jet combustion chamber.

In the housing of a known jet engine, there is a compressor, a turbine, a combustion chamber, an air intake, a jet nozzle, a straightening apparatus, power, ignition and engine start systems.

A combined aircraft engine is known, made by a two-stage gas turbine engine with internal and external shafts, two compressor stages, a main combustion chamber, a turbine, a jet nozzle and a Stirling engine installed in front of the turbine on the internal shaft, in front of which there is an additional combustion chamber.

This engine is equipped with a complex, heavy and bulky design, which is considered its drawback.

Source of information: patent RU No. 2372509, F02K 7/16.

A close technical solution to the claimed object includes a jet engine with a separate version of the turbocompressor and ramjet combustion chambers, comprising a housing with an air intake, a compressor with a guiding apparatus, a gas turbine engine and a jet nozzle.

In this engine, the direct-flow combustion chamber is commensurate with the dimensions of the hollow shaft of the turbocharger, which is considered its drawback.

Source of information: patent RU No. 2162957, F02K 7/16.

The objective of the invention is to create a jet engine with low weight, dimensions, drag, fuel consumption, reliable with a long service life.

The task is achieved by the fact that in the housing of the device there is a combustion chamber, compressor, gas turbine engine (see patent RU No. 2478804 C2), a straightening device, a jet nozzle, an air intake, two rows of controllable shutter dampers along the circumference of the housing before entering the combustion chamber, system power, ignition and engine start.

In the housing of the jet engine there is an air intake, a compressor with a straightening device, a gas turbine engine, followed by a combustion chamber with controlled external and internal shutter dampers installed around the circumference of the engine casing in front of its entrance.

The engine device is illustrated in FIG. 1 in a section with different positions of the external and internal air flaps of the combustion chamber, with the following order of details: housing 1, shaft 2, rotor of the axial compressor 3, blades 4, gas turbine engine 5, exhaust pipes 6, air intake 7, controllable internal air shutter 8 , external 9, a combustion chamber 10, an annular dividing wall with a flame stabilizer 11, an air intake 12, blades of a straightening apparatus 13, a flow line 14, a jet nozzle 15.

The operation of the jet engine is carried out after starting the gas turbine engine 5, which rotates the shaft 2 with the compressor 3, and it creates the movement of air flow from the air intake 12 through the straightening apparatus 13 and along the flow line 14 to the combustion chamber 10, this path is traced on the upper part of FIG. .1 with air dampers 8, 9 located along the housing 1, and where part of the air through the visor 7 follows for the operation of the gas turbine engine 5, such an engine operation process is carried out in the compressor mode.

In the direct-flow engine operation mode, the internal air dampers 8 are pressed against the visor 7 and the compressor air pressure is directed to the gas turbine engine 5, ensuring its operation, and the external air dampers 9 are opened and the oncoming high-speed air pressure is directed to the combustion chamber 10, which corresponds to the lower position of FIG. .one.

However, for a smooth and reliable transition of work from one mode to another, an intermediate operation is provided in which the internal shutters 8 are fixed in the middle position opposite the annular partition 11 of the combustion chamber 10, and the external shutters 9 are open and the engine should be operated in both modes.

Claims (1)

An air-jet engine comprising a housing with an air intake, a compressor with a straightening device, a gas turbine engine, a jet nozzle, characterized in that the engine comprising an air intake, a compressor with a straightening device, a gas turbine engine, followed by a combustion chamber with the circumference of the engine housing in front of it input controlled by external and internal shutter dampers.

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