RU2287114C1 - Tubular-annular combustion chamber of gas-turbine engine - Google Patents

Abstract

FIELD: combustion chambers.

SUBSTANCE: the tubular-annular combustion chamber has an annular cavity formed by the outer and inner walls, flame tubes interconnected by flametransferring pipe connections, having a swirler, combustion zone, mixing zone and a spark plug. The tubular-annular combustion chamber is made for burning of a hydrogen-oxygen mixture. The annular cavity formed by the inner and outer walls is sealed preventing the ingress of the hydrogen-oxygen mixture, and is provided with injectors made for control of the supply of liquid fuel cooling the flame tube and then the combustion products. Each flame tube is made for a detachable and sealed fastening to the outlet annular connection of the compressor.

EFFECT: enhanced economical and ecological efficiency of the tubular-annular combustion chamber.

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Description

The invention relates to the field of engine building, namely to combustion chambers, and can be used in gas turbine engines.

A well-known combustion chamber of a jet engine, it runs on liquid petroleum fuel mixed with air, contains a housing in the cavity of which a flame tube is installed with a nozzle, a combustion stabilizer, a combustion zone and a mixing zone / A.с. USSR No. 705211, F 23 B 3/14, 01/10/1980 / [1].

The disadvantages of the known combustion chamber are the work on expensive petroleum fuels and environmental pollution with toxic exhaust.

Closest to the proposed invention is a tubular-annular combustion chamber of a gas turbine engine, it contains an annular cavity formed by the inner and outer walls, between which are flame tubes, interconnected by flame retardant tubes, having a swirl, combustion zone, mixing zone and spark plug / Rytvinsky G.N. Meet the engine. - M.: Engineering, 1993, pp. 37-41, Fig. 23 / [2].

The disadvantages of the closest analogue are the high cost of the fuel used, environmental pollution by toxic emissions and its inappropriateness for burning a hydrogen-oxygen mixture.

The technical problem solved by the invention is to increase the economic and environmental efficiency of the combustion chamber of a gas turbine engine.

The problem is solved in that in a tubular-annular combustion chamber of a gas turbine engine containing an annular cavity formed by inner and outer walls, between which are flame tubes, interconnected by flame-retardant tubes, having a swirl, for example, a blade, a combustion zone, a mixing zone and a candle ignition, according to the invention, the combustion chamber is configured to burn a hydrogen-oxygen mixture. Where the annular cavity formed by the inner and outer walls is sealed from the ingress of a hydrogen-oxygen mixture and is equipped with nozzles adapted to be controlled, for example, by a control unit for supplying a cooling heat pipe to it and then liquid combustion products, such as water. Each flame tube is made with the possibility of its detachable and hermetic fastening to the outlet ring pipe of the compressor, for example, bolts.

The invention is shown in the drawings, where:

figure 1 - schematic section of a combustion chamber,

figure 2 is a view along arrow a in figure 1,

figure 3 is a view along arrow B in figure 1.

An example of the implementation of the proposed solution.

The tubular-annular combustion chamber of a gas turbine engine contains an annular cavity 1 / Fig. 1-3/, sealed from the ingress of a hydrogen-oxygen mixture, formed by inner 2 and outer 3 walls, for example, bolts fixed to the annular flanges of the compressor and turbine, between which are located flame tubes 4 interconnected by flame-retardant nozzles 5 having a swirl 6, for example, a blade, a combustion zone 7, a mixing zone with holes 8 and a spark plug 9. The annular cavity is equipped with nozzles 10 for I am controlled, for example, by a control unit for supplying cooling pipes to it and then the products of fuel combustion in the mixing zone of a liquid, for example water. Each flame tube is detachable and hermetically, for example, bolted, by flanges 11 is attached to the output annular pipe 12 of the compressor, its temperature expansion occurs towards the turbine 13.

The tubular-annular combustion chamber of a gas turbine engine operates as follows.

Before starting, the spark plug 9 is turned on and the fixed flame tubes 4 are inserted through the compressor nozzle 12 into the flanges 11 through, for example, a blade swirler 6, which turbulizes the flow, the hydrogen-oxygen mixture falls. In the combustion zone 7, the candle 9 ignites the gas mixture, through the flame retardant nozzles 5 the flame propagates into the adjacent flame tubes 4. The swirl 6 due to the pressure, gas flow rate and low intrinsic temperature cuts off the flame during reverse impacts from the combustion zone 7. Through nozzles 10 in the sealed cavity 1 of the combustion chamber, under the control of, for example, a control unit, liquid is supplied, for example water, which cools the flame tubes 4 and then enters the mixing zone through the openings 8 through the openings 8 and cools there fuel combustion ducts to a predetermined value.

The proposed combustion chamber in operation is highly economical and absolutely environmentally friendly; it will find wide application in gas turbine engines for various purposes.

Claims (1)

A tubular-annular combustion chamber of a gas turbine engine, containing an annular cavity formed by inner and outer walls, between which are flame tubes, interconnected by flame-sparging nozzles, having a swirler, a combustion zone, a mixing zone and a spark plug, characterized in that it is capable of burning hydrogen-oxygen mixture, where the annular cavity formed by the inner and outer walls is sealed from the ingress of the hydrogen-oxygen mixture and is equipped with force nkami, adapted to supply a controlled cooling it and then the flame tubes of the combustion of liquid fuel products, each flame tube is arranged to be releasably and sealingly attaching the conduit to the outlet ring compressor.

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