RU2786843C1 - Gas turbine engine - Google Patents

Abstract

FIELD: gas turbine engines.

SUBSTANCE: invention relates to gas turbine engines. The gas turbine engine contains an inlet device, a compressor, a turbine, an annular combustion chamber with nozzles, a 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 supplying cooling air. Holes for supplying cooling air are made with flanges; through the longitudinal axis of the annular combustion chamber.

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

1 cl, 6 dwg

Description

The invention relates to gas turbine engines - GTE.

Known gas turbine engine according to the RF patent for invention No. 2193099, IPC F02K 3/100, publ. November 20, 2002

This gas turbine engine contains a casing, a compressor, a turbine, a main combustion chamber connected by an air path to the compressor.

Disadvantages uneven circumferential temperature field at the outlet of the combustion chamber and relatively low combustion efficiency.

Known gas turbine engine according to the RF patent for the invention No. 2562822, IPC F02K 7/16, publ. 07/20/2015, prototype.

This gas turbine engine contains a compressor, a combustion chamber with a flame tube and nozzles on the nozzle plate, a flame tube with an outer shell of the flame tube, communicating the outer annular gap between the outer shell of the flame tube and the outer casing of the chamber with a chamber of the flame and a turbine containing at least one stage with nozzle apparatus and impeller.

The use of an annular combustion chamber has advantages over tubular and tubular-annular chambers:

- smaller dimensions of the combustion chamber,

- less weight

- slightly better temperature field at the exit from 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 is to increase the efficiency of the engine and reduce 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 a gas turbine engine containing an inlet device, a compressor, a turbine, an annular combustion chamber with nozzles, a 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 supplying cooling air, the fact that the holes for supplying cooling air are made with flanges, the flame tube is equipped with pockets for supplying air and is made with the possibility of swirling the combustion products relative to the longitudinal axis of the combustion chamber, due to the simultaneous placement of nozzles on the nozzle plate, holes for supplying cooling air and pockets at an angle to a plane passing through the longitudinal axis of the annular combustion chamber.

The essence of the invention is illustrated in Fig. 1…6, where:

in fig. 1 shows a schematic diagram of a gas turbine engine,

in fig. 2 shows an annular combustion chamber,

in fig. 3 shows view A in FIG. 2,

in fig. 4 shows view B in FIG. 3,

in fig. 5 shows section C-C in FIG. 2

in fig. 6 shows section D - D in FIG. 2

The list of features accepted in the description:

input device 1,

compressor 2,

guide apparatus 3.

compressor impeller 4,

annular combustion chamber 5,

flame tube 6,

outer casing 7,

external annular gap 8,

camera body 9,

the cavity of the flame tube 10.

nozzle plate 11,

nozzle 12

manifold 13,

fuel system 14,

turbine 15,

nozzle apparatus 16,

turbine impeller 17,

exhaust device 18.

cavity 19,

shaft 20,

support 21,

holes for cooling air supply 22,

flanging 23,

pocket 24,

perforation 25,

air holes 26.

The proposed gas turbine engine - gas turbine engine of increased efficiency contains an input device 1, a compressor 2 with guide vanes 3 and compressor wheels 4, an annular combustion chamber 5 with a flame tube 6 with an outer casing 7 of the flame tube 6, communicating an external annular gap 8 between the outer casing 7 of the flame pipes 6 and the chamber body 9 with the cavity of the flame tube 10.

At the inlet end of the flame tube 6 there is a nozzle plate 11 with injectors 12 and a manifold 13, to the inlet of which the fuel system 14 is connected.

A turbine 15 is connected to the outlet of the annular combustion chamber 5, containing at least one stage with a nozzle apparatus 16 and a turbine wheel 17.

An exhaust device 18 is connected to the outlet of the turbine 15.

The air path includes an inlet 1 and a cavity 19 between the compressor 2 and the annular combustion chamber 5.

Shaft 20 connects compressor impellers 4 and turbine impeller 17 and is mounted on supports 21. There can be more than two supports 21.

On the flame tube 6 there are holes for supplying cooling air 22 with flanges 23 and pockets 24 for throwing cooling air into the flame tube 6 to a considerable depth. The flanges 23 of the holes for supplying cooling air 22 are designed to create the direction of the cooling air in order to swirl it along the axis 00 of the annular combustion chamber 4. The pockets 24 are perforated 25 to cool them.

In FIG. 2 shows an annular combustion chamber.

In FIG. 3 shows view A of nozzle 12.

In FIG. 4 shows view B of the nozzles 12 and the nozzle plate 11. The nozzle plate 11 is stepped on the inside, and the nozzles 12 are installed in such a way that their axes O ₁ O ₁ are inclined to the longitudinal axis of the combustion chamber OO at an angle ϕ. Optimum angle of inclination ϕ=30…60°.

In FIG. 5 shows a section C-C of the holes for supplying cooling air 22. FIG. 4 it can be seen that the air passing through the holes for supplying cooling air 22 twists along the inner wall of the outer casing 7. This is achieved by making flanges 23 at an angle ϕ ₁ to the longitudinal axis of the annular combustion chamber OO.

But the combustion products inside the annular combustion chamber 5 do not twist.

The optimal installation angle of the flanges to the plane OO passing through the longitudinal axis of the annular combustion chamber ϕ ₁ =30...60°.

In FIG. Figure 6 shows a variant of swirling the combustion products in the entire volume of the annular combustion chamber 5. This was achieved by using pockets 24 that protrude significantly into the flame tube 6 and whose axes are inclined to the planes passing through the longitudinal axis of the annular combustion chamber OO at an angle ϕ ₂ .

The optimal installation angle of the pockets 24 to the plane passing through the longitudinal axis OO of the annular chamber ϕ ₂ =7…30°

GAS TURBINE ENGINE OPERATION

When the gas turbine engine is started (Fig. 1…6), the starter (not shown) spins the shaft 20, which spins the impellers of the compressor 4.

When starting the gas turbine engine, fuel gas enters the fuel manifold 13 and then to the injectors 12 (Fig. 1).

The nozzles 12 are fuel-air and the air necessary for combustion enters through the air supply holes 26 made in the nozzle plate 11.

The air for cooling the flame tube 6 also passes through the holes for supplying cooling air 22 with flanges 23. The main part of the air enters through the pockets 24 to a considerable depth inside the flame tube 6 and also twists. The perforation 25 is designed to create a film cooling of the pockets 24 themselves.

All swirl means swirl the air and combustion products in the annular combustion chamber 5 in one direction. This will improve the combustion process and increase the completeness of combustion and reduce the emission of harmful substances.

In addition, the circumferential unevenness of the temperature field at the outlet of the annular combustion chamber will decrease.

Significant swirling of the flow relative to the longitudinal axis OO of the annular combustion chamber will simplify the design of the first turbine nozzle apparatus and, if necessary, refuse to cool it, for example, by using ceramics.

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)

A gas turbine engine containing an inlet device, a compressor, a turbine, an annular combustion chamber with nozzles, a 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, characterized in that that the holes for supplying cooling air are made with flanges, the flame tube is equipped with pockets for supplying air and is made with the possibility of swirling the combustion products relative to the longitudinal axis of the combustion chamber due to the simultaneous placement of nozzles on the nozzle plate, holes for supplying cooling air and pockets at an angle to the plane, passing through the longitudinal axis of the annular combustion chamber.

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