RU2289758C1 - Tubular-annular combustion chamber of gas-turbine engine - Google Patents

Abstract

FIELD: gas-turbine engines.

SUBSTANCE: proposed tubular-annular combustion chamber of gas-turbine engine has annular cavity formed by internal and external walls with flame tubes placed in-between; these tubes are intercommunicating through flame-transfer pipes; flame tubes are provided with swirler, combustion zone, mixing zone, and spark plug. Combustion chamber is designed to burn hydrogen-oxygen mixture. Annular cavity formed by internal and external walls is sealed to prevent ingress of hydrogen-oxygen mixture and has injectors for controlled supply of flame-tube cooling liquid and then fuel combustion products therein. Each flame tube is designed for split and tight fixation to outlet annular manifold of compressor. Swirler is made in the form of conical or spherical shut-off device mounted in each flame tube for axial displacement of its working element to open-close positions.

EFFECT: enhanced economic efficiency and environmental friendliness.

1 cl, 4 dwg

Description

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

A well-known combustion chamber of a jet engine, runs on liquid fuel mixed with air, contains a housing in the cavity of which a flame tube with a nozzle is installed. combustion stabilizers, combustion zone, and mixing zone.

/ A.s. USSR, No. 705211, F 23 R 3/14, 01/10/1980 / [1].

A disadvantage of the known combustion chamber is its operation on expensive petroleum fuels and environmental pollution with toxic emissions.

Closest to the proposed invention is a tubular-annular combustion chamber of a gas turbine engine, contains an annular cavity formed by inner and outer walls, between which are flame tubes, interconnected by flame retardant tubes having a swirler, a combustion zone, a mixing zone and a spark plug.

/ Rytvinsky G.N. Meet the engine. - M .: Engineering, 1993, p. 37-41, Fig. 23. / [2].

The disadvantage of the closest analogue is 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 swirler, a combustion zone, a mixing zone and a spark plug. 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 configured to be controlled, for example, by a control unit. supplying cooling chimney pipes to it and then liquid combustion products, for example, water. Each flame tube is made with the possibility of its detachable and hermetic fastening, for example, on bolts, to the outlet ring pipe of the compressor. The swirl is made in the form of a conical or spherical shape of a cutter, for example, a check valve installed in each flame tube with the possibility of axial movement of its working body in the open - closed position,

The invention is shown in the drawings, where

Figure 1 is a schematic sectional view 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.

Figure 4 is a schematic sectional view of a spherical cutter,

An example of the implementation of the proposed solution.

The tubular-annular combustion chamber of a gas turbine engine contains an annular cavity 1 sealed from the ingress of a hydrogen-oxygen mixture 1 / Fig. 1-4/, formed by inner 2 and outer 3 walls, for example, bolted to the annular flanges of the compressor 4 and turbine 5, between which are the flame tubes 6, interconnected by flame-retardant nozzles 7, having either a conical or spherical shape shut-off 8, for example a check valve, where the working body of the shut-off takes open positions - behind indoor, combustion zone 9. mixing zone with holes 10 and spark plug 11. The annular cavity is equipped with nozzles 12 for controlling, for example, a control unit, supplying cooling heat pipes to it and then fuel combustion products in the liquid mixing zone, for example water. Each flame tube is detachable and hermetically, for example, on bolts, with its flanges 13 attached to the compressor outlet ring pipe, its temperature expansion occurs towards the turbine.

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

Before starting, the spark plug 11 / Fig. 1-4/ is turned on and a hydrogen-oxygen mixture is fed into the flame tubes 6 through a cut-off device 8, for example, of a conical shape, from the compressor, through its output annular branch pipe with an annular flange 4. The flow pressure overcomes the spring resistance of the shut-off valve 8 and its working body moves to the open position and passes the gas mixture into the combustion zone 9 of the flame tube 6. The cut-off valve 8 at the beginning of the combustion zone 9 forms a zone with reduced pressure, the reverse gas flow and turbulent flow. In addition, the cutter 8, in case of possible explosions, reverse impacts in the combustion zone 9 of the flame tube 6, closes the return stroke to the combustion products and protects the compressor from destruction. Through nozzles 12 into the annular cavity 1 of the combustion chamber sealed from the ingress of hydrogen-oxygen mixture, under the control of, for example, a control unit, a liquid is supplied, for example water, which cools the walls of the flame tubes 6 and then enters the mixing zone through the openings 10 in the form of steam and cools the products of fuel combustion there to a predetermined value. Heat pipes 6 are detachable and tight. with their flanges 13, for example, are bolted to the outlet annular pipe with the compressor flange 4, thermal expansion occurs towards the turbine flange 5.

The proposed combustion chamber in operation is highly economical and absolutely safe for the environment; 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 communicated with flame retardant tubes, having a swirl, 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 a hydrogen-oxygen mixture and is equipped with nozzles by means of which the cooling chimney tubes and then the products of fuel fuel combustion are controlled to be fed into it, each flame tube is made with the possibility of its detachable and hermetic fastening to the compressor output ring pipe, the swirler is made in the form of a conical or spherical shape of a cutter installed in each flame pipe with the possibility of axial movement of its working body in the open-closed position.

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