RU2783576C1 - Annular combustion chamber of a gas turbine engine - Google Patents

Abstract

FIELD: engine building.

SUBSTANCE: invention relates to gas turbine engines. Annular combustion chamber of a gas turbine engine comprises a body, a nozzle plate with nozzles, a flue tube with an external flue tube casing, an annular gap between the external flue tube casing and the combustion chamber body, in communication with the cavity of the heat pipe; the flue tube is provided with holes for the supply of cooling air and pockets for air supply, and is configured to swirl the combustion products relative to the longitudinal axis of the combustion chamber. The possibility of swirling the combustion products is provided by the simultaneous placement of the nozzles on the nozzle plate and the holes for the supply of cooling air at an angle to the plane passing through the longitudinal axis of the annular combustion chamber.

EFFECT: reduced circumferential unevenness of the temperature field at the output of the combustion chamber.

1 cl, 5 dwg

Description

The invention relates to the combustion chambers of gas turbine engines - gas turbine engines.

Known gas turbine engine according to the RF patent for the invention No. 2493492, IPC F23R 3/28, publ. 20.09.2013

The GTE combustion chamber contains a housing, a flame tube having outer and inner walls and an annular plate with injector modules installed on it and a main fuel manifold connected to the plate, the cavity of which is connected by fuel channels with injector modules, outer and inner housings, outer and inner casing, installed with a gap relative to the outer and inner casings. The number of injector modules is a multiple of four

Disadvantages: low completeness of fuel combustion in the combustion chamber and emission of harmful substances in exhaust gases.

Known gas turbine engine according to the RF patent for the invention No. 2493495, IPC F23R 3/00, publ. 09/20/2013, prototype.

SUBSTANCE: annular combustion chamber of a gas turbine engine comprises a housing, a nozzle plate with injectors, a flame tube with an outer casing of the flame tube, communicating the outer annular gap between the outer shell, an annular gap between the outer shell of the flame tube and the combustion chamber body, communicating with the cavity of the flame tube, the flame tube provided with holes for supplying cooling air and pockets for supplying air, and is configured to swirl combustion products relative to the longitudinal axis of the combustion chamber,

Disadvantage: low completeness of fuel combustion in the combustion chamber and emission of harmful substances in exhaust gases.

The objectives of the invention: increasing the efficiency of the engine and reducing the circumferential unevenness of the temperature field at the outlet of the combustion chamber.

Achieved technical results: increasing the efficiency of the engine and reducing the circumferential unevenness of the temperature field at the outlet of the combustion chamber.

The solution of these problems is achieved in the annular combustion chamber of a gas turbine engine, containing a housing, a nozzle plate with nozzles, a flame tube with an outer casing of the flame tube, an annular gap between the outer casing of the flame tube and the combustion chamber housing, which communicates with the cavity of the flame tube, the flame tube is provided with holes for supply of cooling air and pockets for air supply, and is made with the possibility of swirling the combustion products relative to the longitudinal axis of the combustion chamber. According to the invention, the possibility of swirling the combustion products is made due to the simultaneous placement of nozzles on the nozzle plate, and holes for supplying cooling air at an angle to the plane passing through the longitudinal axis of the annular combustion chamber.

The possibility of swirling the combustion products can be made by placing nozzles on the nozzle plate at an angle to the plane passing through the longitudinal axis of the annular combustion chamber and by placing the flame tube cooling holes at an angle to the plane passing through the longitudinal axis of the annular combustion chamber.

The essence of the invention is illustrated in Fig. 1…5, where:

in fig. 1 shows the annular combustion chamber of a gas turbine engine,

in fig. 2 shows view A,

in fig. 3 shows view B,

in fig. 4 shows the section C-C,

in fig. 5 shows a section B-B.

The list of features accepted in the description:

flame tube 1,

outer casing 2 of the flame tube 1,

external annular gap 3,

camera body 4,

the cavity of the flame tube 5,

nozzle plate 6,

nozzle 7,

manifold 8,

fuel system 9,

cavity 10,

openings for supplying cooling air 11,

flanging 12,

air pockets 13,

perforation. fourteen,

air holes 15,

ϕ ₁ - the angle of inclination of the nozzles,

ϕ ₂ - the angle of inclination of the flanges,

ϕ ₃ - the angle of inclination of the air supply pockets.

An annular combustion chamber of a gas turbine engine - gas turbine engine of increased efficiency (Fig. 1) is proposed that contains a flame tube 1 with an external casing of the flame tube 2, communicating an external annular gap 3 between the outer casing 2 of the flame tube 1 and the chamber body 4 with the cavity of the flame tube 5.

At the inlet end of the flame tube 1 (Fig. 2) there is a nozzle plate 6 with injectors 7 and a manifold 8, to the inlet of which the fuel system 9 is connected.

The air path includes a cavity 10 (Fig. 1) between the compressor (not shown in Fig. 1-5) and the annular combustion chamber.

On the flame tube 1 there are holes 11 for supplying cooling air with flanges 12 and pockets 13 for throwing cooling air into the cavity 5 of the flame tube 1 to a considerable depth.

Flanges 12 of holes 11 for supplying cooling air (Fig. 4) are designed to create the direction of the cooling air in order to swirl it along the axis OO of the annular combustion chamber within the boundary layer.

The air supply pockets 13 (FIG. 5) are perforated. 14 for cooling pockets 13.

In FIG. 3 shows view B of nozzles 7 and nozzle plate 6. The nozzle plate 6 is stepped on the inside, and nozzles 7 are installed so that their axes O ₁ O ₁ are inclined to the longitudinal axis of the combustion chamber OO at an angle ϕ ₁ . The optimal angle of inclination ϕ ₁ =7…30°.

In FIG. 4 shows a section C-C of holes 11 for supplying cooling air. In FIG. 4 it can be seen that the air passing through the holes 11 for supplying cooling air is twisted along the outer casing 2 of the flame tube 1. This is achieved by making flanges 12 at an angle ϕ ₂ =7...30° to the longitudinal axis of the combustion chamber OO. But the products of combustion inside the annular combustion chamber do not twist.

Optimum angle ϕ ₂ =7…30°

In FIG. 5 shows a section B-B of the swirl of combustion products in the entire volume of the annular combustion chamber. This is achieved by using pockets 13 for air supply, significantly protruding into the flame tube 1 and the axes of which are inclined to the planes passing through the longitudinal axis of the annular combustion chamber RO at an angle ϕ ₃ .

Optimum angle ϕ ₃ =7…30°

The pockets 13 for supplying air 13 comprise perforations 14 for air. The air perforation 14 is designed to cool the air supply pockets 13.

OPERATION OF THE ANNULAR COMBUSTION CHAMBER OF A GAS TURBINE ENGINE

When starting a gas turbine engine (Fig. 1...5), a starter (not shown) spins a shaft that spins the impellers of the compressor and turbine (not shown).

When starting the gas turbine engine, fuel gas enters the fuel system 9, then into the manifold 8 and then into the injectors 7 (Fig. 1). The fuel is mixed with air, which enters the nozzles 7 through holes 15.

Nozzles 7 are fuel-air and the air necessary for fuel combustion enters through air holes 15 (Fig. 1, 2 and 3) made in the nozzle plate 6 and in the nozzles 7.

As a result, the entire volume of combustion products is intensively swirled and the fuel burns out the cavity of the flame tube 5 more completely.

This made it possible to increase the completeness of combustion and reduce the circumferential unevenness of the temperature field at the outlet of the combustion chamber.

The application of the invention allowed:

- increase the completeness of fuel combustion in the combustion chamber,

- reduce the emission of harmful substances,

- reduce the circumferential non-uniformity of the temperature field at the outlet of the annular combustion chamber by swirling the combustion products in the annular combustion chamber by the proposed means,

- simplify the design of the first turbine nozzle apparatus and, if necessary, refuse to cool it, for example, by using ceramics.

Claims (1)

An annular combustion chamber of a gas turbine engine, comprising a housing, a nozzle plate with nozzles, a flame tube with an outer casing of the flame tube, an annular gap between the outer casing of the flame tube and the combustion chamber body, communicating with the cavity of the flame tube, the flame tube is provided with holes for supplying cooling air and pockets for air supply and is made with the possibility of swirling the combustion products relative to the longitudinal axis of the combustion chamber, characterized in that the possibility of swirling the combustion products is made due to the simultaneous placement of nozzles on the nozzle plate and holes for supplying cooling air at an angle to the plane passing through the longitudinal axis of the annular chamber combustion.

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