Combustion chamber for gas turbine engine

FIELD: gas turbine engine engineering.

SUBSTANCE: combustion chamber comprises housing provided with inner and outer ring shells, device for graduate change of the ratio of areas of the cross-sections of primary and secondary passages, and collector stabilizer. The reaction zone has shutters and inserts that define inner and outer rings. The shutters and inserts are pivotally interconnected for permitting change of the area of the cross-section in radial direction. The collector stabilizer is unmovable.

EFFECT: enhanced reliability.

4 dwg

 

The invention relates to the turbines, namely the annular combustion chambers of gas-turbine engines (GTE).

A device for burning fuel gas-turbine engine comprising a housing with an annular inner and outer shells and the actuator. In the reactor area includes stationary and movable relative to the first circumferential direction separators flow, forming alternating primary and secondary channels with a variable ratio of the areas of flow sections. In a stationary flow dividers provided with channels for supplying a fuel to the fuel reservoir, stabilizers flame, to the inlet of the primary channels and consisting of fixed and moving parts are telescopically interconnected and rigidly fixed respectively on the fixed and movable dividers flows [1].

The disadvantage of this combustion chamber (COP)adopted for the prototype is uneven distributions of temperature at the outlet of the COP in the axial and radial directions, associated with the presence of alternating primary and secondary channels formed by the separators flows, which reduces the service life of the gas turbine. In addition, in design, made in the form of sectors, to ensure effective mixing of the air-fuel mixture is required, the length of the mixing zone COP, which leads to increase the main sizes.

An object of the invention is the improvement of the prototype, namely improving the resource of the gas turbine by providing uniform distributions of temperature and decrease of the mixing zone in the COP.

The essence of the invention lies in the fact that in the combustion chamber, comprising a housing with an annular inner and outer shells, a device for continuous change of the ratio of the area of flow cross-sections of primary and secondary canals and collector-stabilizer, installed shutters and spacers inner and outer rings forming the primary and secondary zones. Shutters and bars pivotally connected with the possibility of relative displacement in the radial direction. In addition, the collector-stabilizer flame, which is a supply of fuel is performed in a closed loop fixed.

The technical result of the invention is to increase the service life of the gas turbine and the reduction of the mixing zone, affecting the dimensions of the COP, which is achieved by the improvement of devices for continuous change of the ratio of the area of flow cross-sections of the primary and secondary channels and installation, pivoted between the wings and spacers, forming the inner and outer rings, and the collector-stabilizer, performed in a closed loop fixed. This con is traccia eliminates the division of reactor zone in the sector.

Comparison with the prototype of the proposed solution allows to conclude that there is a significant distinguishing characteristics that affect the result of the invention:

- hinged between a sash and spacers forming the inner and outer rings;

- fixed fuel manifold stabilizer is performed in a closed loop, which allows to make a conclusion about the presence of patentability criterion of "novelty".

In the known technical solutions these distinctive characteristics have been identified that meet the criteria of the invention "significant differences".

Figure 1 shows the combustion chamber of a gas turbine engine, a longitudinal section; figure 2 - cross section A-a in figure 1; figure 3(a) diagram of the relative position of the valves and shims corresponding to the minimum mode of operation; 3(b) is the same, corresponding to the maximum mode; figure 4 is a view along arrow B in figure 2.

The combustion chamber of the CCD (figure 1) includes a housing with inner ring 1 and outer 2 rings forming the reactor zone 3 and the mixing zone 4. Reactor zone 3 (figure 2) are divided into primary 5 and secondary 6 zone through the valves 7 and spacers 8 forming the inner and outer rings, and spacers with holes 11 (figure 4) to ensure their cooling and effective organization of the working process Gorani is in the reactor zone. Sash 7 and spacers 8 have the possibility of relative displacement in the radial direction by hydraulic actuators 9 (figure 2). Supply of fuel is carried out in a fixed collector-stabilizer 10, performed in a closed loop.

The combustor operates as follows: when operating the CCD at higher modes, when the sash 7 and spacers 8 of the inner and outer rings close tightly over the surface of the inner and outer shells of the primary zone 5 has a maximum throughput figb), providing a maximum flow of primary air. When the engine on lower modes (figa) smoothly decreases throughput in the primary zone 5 and, consequently, increase throughput in the secondary zone 6, thereby redistributing the air flow rate in favor of the secondary. To do this, using the actuator 9 moves the sash 7 and spacers 8 of the inner and outer rings in the direction corresponding to the decrease in throughput in the primary zone 5.

Such a device main combustion chambers ensures that the composition of the mixture in the primary zone at the optimum level throughout the range of engine operating conditions and operating conditions and ensures uniformity of the field temperature in the outlet section of the combustion chamber, and also intensifies% the SS mixing of air-fuel mixture through the use of the entire volume of the COP.

The source of information

1. A method of burning fuel in high temperature gas turbine engine and a device for burning fuel in a gas turbine engine. RF patent №2124676, CL F23R 3/26, publ. 10.01.99,, bull.№1 (prototype).

The combustion chamber of a gas turbine engine, comprising a housing with an annular inner and outer shells, a device for continuous change of the ratio of the area of flow cross-sections of primary and secondary canals and collector-stabilizer, characterized in that the reactor area has a sash and spacers forming the inner and outer rings, and the leaf and spacers pivotally interconnected with the possibility of changing the ratio of the cross-section area in the radial direction, and the collector-stabilizer is made in a closed loop fixed.



 

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