Annular combustion chamber of a gas turbine engine

 

Annular combustion chamber of a gas turbine engine includes a housing and a fixed fuel manifold with nozzles made in the form of two shells forming the channels of the first and second stages. Each of the channels is in communication with the channel of the two-stage nozzle. The covers are placed coaxially. The inner casing is made in the form of two interconnected side walls and the base, forming one piece with the nozzle body. The outer casing is made in the form of a cover connected to the base. This embodiment of the device prevents the formation of coke in the channel of the first cascade of the fuel manifold and the fuel elements of the nozzles of the first stage, which allows to increase the service life of the combustion chamber. 4 C.p. f-crystals, 4 Il.

The invention relates to the field of aircraft engine industry, namely the design of the fuel manifold of the combustion chamber GTE.

Known annular combustion chamber of a gas-turbine engine comprising a housing and a fixed fuel manifold with injectors [1].

Of the known devices is closest to the invention is annular combustion chamber of a gas-turbine engine comprising a housing and a fixed fuel manifold with nozzles made in view of the crimson two-stage injector [2].

A disadvantage of the known devices is the formation of coke in the channel of the first cascade of the fuel manifold and nozzles. This is due to the large heating the hydrocarbon fuel and its thermal decomposition when blowing air with a high temperature at the inlet into the combustion chamber.

Coking of the fuel leads to an increase in the hydraulic resistance of the collector, the deterioration of the start-up and other operational characteristics of the combustion chamber GTE.

Object of the invention is to prevent the formation of coke in the channels of the first stage fuel manifold and nozzles of the first stage.

This task is solved in that the annular combustion chamber of a gas-turbine engine comprising a housing and a fixed fuel manifold with nozzles made in the form of two shells forming the channels of the first and second stages, each of which is communicated with the corresponding channel of the two-stage nozzles, shrouds installed coaxially, while the inner casing is made in the form of two interconnected side walls and the base, forming one piece with the nozzle body, and an outer casing in the form of a cover connected to the base.

This embodiment of the device before the pout cascade by cooling the fuel channel of the second cascade and lack of contact with the stream of hot air entering the combustion chamber.

In Fig.1 shows a longitudinal section of an annular combustion chamber GTE;

in Fig.2, 3, 4 - embodiments of the fuel manifold of the combustion chamber.

Annular combustor includes a housing 1 and a fixed fuel manifold with 2 nozzles 3.

In case 4 injectors provided with channels 5 and 6 of the first and second stages. Fuel collector 2 made in the form of inner and outer housings 7 and 8 installed coaxially.

The inner casing 7 made in the form of two interconnected by welding the side walls 9 and the base 10, forming one piece with the housing 4 of the nozzle 3 and forming the channel 11 of the first cascade is provided with a channel 5 of the first stage nozzle. The outer casing 8 of the fuel reservoir 2 made in the form of caps connected by welding with the base 10 and forming the channel 12 of the second cascade, communicated with the channel 6 of the second stage nozzle 3.

The inner casing 7 may be made in the form of a curved shell 13 (Fig.2) or rectangular shell 14 (Fig.3) attached by welding to the base 10.

The fuel manifold 2 may be equipped with a screen 15 (Fig.3) covering an outer casing 8 forming with it an air cavity 16 and serves to reduce heating fuel channel 11 Pervov the t to be filled with insulating material to further reduce fuel heating in the channels 11, 12 first and second stages of the fuel reservoir 2 (Fig.4).

When the engine is running the fuel flows into the channel 11 of the first stage fuel manifold 2, and then into channel 5 of the first stage nozzle connected to the nozzle 17, through which the fuel is injected into the combustion zone. Then the fuel flows into the channel 12 of the second cascade of the fuel manifold 2, passes into the channel 6 of the second stage nozzle connected to a nozzle 18 through which fuel is injected into the combustion zone.

The proposed device provides cooling the fuel channel of the second cascade and prevents contact of the structural elements at the entrance to the combustion chamber with a stream of hot air, which prevents the formation of coke in the channel of the first cascade of the fuel manifold and the fuel elements of the nozzles of the first stage.

The proposed design allows to make the channels of the first and second stages of the fuel manifold of the combustion chamber by turning with subsequent grinding of surfaces with high purity, which further reduces the formation of coke. In addition, the reduced number of joints, which increases the reliability of the collector.

The invention allows to improve operational performance and increase re 29.07.68.

2. “The construction and design of aircraft gas turbine engines” under the General editorship of Dr technology. Sciences D. C. Hanina, M., "engineering", 1989, page 420.

Claims

1. Annular combustion chamber of a gas turbine engine, comprising a housing and a fixed fuel manifold with nozzles made in the form of two shells forming the channels of the first and second stages, each of which is communicated with the corresponding channel of the two-stage injector, characterized in that the covers are placed coaxially, while the inner casing is made in the form of two interconnected side walls and the base, forming one piece with the nozzle body, and an outer casing in the form of a cover connected to the base.

2. Annular combustion chamber under item 1, characterized in that the inner casing is made in the form of a curved shell attached to the base of the fuel manifold.

3. Annular combustion chamber under item 1, characterized in that the inner casing is made in the form of a rectangular shell attached to the base of the fuel manifold.

4. Annular combustion chamber according to any one of paragraphs.1-3, characterized in that the fuel reservoir is equipped with teplosernaya on p. 4, characterized in that the cavity between the outer shell and the heat-shielding screen filled with insulating material.

 

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