RU2269664C1 - Gas-turbine plant - Google Patents

Abstract

FIELD: electrical installations and vehicles; gas-turbine plants burning fuel combustion products.

SUBSTANCE: proposed gas-turbine plant has compressor, air turbine coupled with compressor shaft, power turbine, combustion chamber, and heat exchanger. In addition, gas-turbine plant has two compressors and two air turbines. Compressors and air turbines are intercoupled and mounted on common shaft in tandem; they are placed in jacket to form space between surfaces of compressors coupled with air turbines and jacket; the latter communicates with inlet of heat exchanger. Outlet of heat exchanger communicates with multiple-tube adapter whose outlets communicate with annular combustion chamber disposed between two power turbines.

EFFECT: enhanced reliability and service life of parts operating at high temperature; reduced fire and explosion hazard.

4 cl, 2 dwg

Description

The invention relates to power and transport installations and relates to gas turbine plants using products of combustion of fuel.

Known gas turbine installation, selected as a prototype (see ed. St. No. 408587, class F 02 C 7/14, filing date 04/11/72, applicant: Moscow Order of the Lenin Aviation Institute named after Sergo Ordzhonikidze).

The known technical solution comprises a compressor unit including a compressor and a pneumatic turbine, a power turbine, a combustion chamber and a heat exchanger installed in front of the compressor. A pneumatic turbine is placed in front of the heat exchanger and mechanically connected to the compressor shaft.

The disadvantage of the known gas turbine installation of the prototype is the low efficiency and reliability.

The objective of the present invention is:

- increase the efficiency of the gas turbine installation;

- improving the reliability and resource of parts operating at high temperature;

- reduction of fire hazard and explosion hazard.

The solution of the problem and the advantages of the claimed invention arise from the following detailed description of the gas turbine installation and an example of their specific implementation.

To solve this problem, a gas turbine installation comprising a compressor, a pneumatic turbine connected to the compressor shaft, a power turbine, a combustion chamber and a heat exchanger, according to the invention, the gas turbine installation further comprises two compressors and two pneumatic turbines, the compressors and pneumatic turbines being interconnected and installed on a single shaft in series, while they are enclosed in a shirt, forming a cavity between the surfaces of compressors with pneumatic turbines and a jacket to which the inlet of the heat exchanger is connected, and its output is connected to a multi-tube transition, the outputs of which are connected to an annular combustion chamber located between two power turbines.

The problem is solved due to the fact that in the gas turbine installation according to the invention, the shaft on which the compressors with pneumatic turbines are mounted is connected to the shaft of the power turbines.

According to the invention, all units are enclosed in a housing, while they are separated from it by a heat shield.

Reducing the power consumption of the compressor can be achieved by multi-stage air compression with intermediate cooling.

As can be seen from the foregoing, distinctive features from the prototype are the presence of three compressors and three pneumatic turbines, interconnected and mounted on a single shaft in series. With such a device of a gas turbine installation, air is cooled during compression, which reduces the compression work, and therefore the power spent on compression of the combustion air. As a result, the efficiency of the gas turbine installation increases.

The presence of a heat exchanger and a multi-tube transition through which low-temperature air flows, heated by exhaust gases, allows to reduce heat loss.

The gas turbine unit is equipped with a casing with a heat shield, through which the temperature of the outer casing is reduced, as a result of which the reliability is increased and the fire hazard and explosion hazard are reduced.

The claimed technical solution compared to the prototype (see ed. St. No. 408587, class F 02 C 7/14, application date 04/11/72, applicant: Moscow Order of the Lenin Aviation Institute named after Sergo Ordzhonikidze) has a new combination essential features, therefore, meets the criterion of "novelty."

The above set of distinctive features and the achieved result characterize the unity of the invention and do not follow explicitly from the studied prior art, that is, they have an inventive step.

The claimed technical solution can be used in industry, therefore, it is industrially applicable.

The essence of the proposed technical solution is illustrated by a description of specific examples of its implementation and the accompanying drawings, where:

- figure 1 shows a gas turbine installation;

- figure 2 is a section aa in figure 1.

Concrete example

The gas turbine installation comprises a compressor 1, a pneumatic turbine 2, a compressor 3, a pneumatic turbine 4, a compressor 5, a pneumatic turbine 6, a heat exchanger 7, power turbines 8, 9, a combustion chamber 10, a heat shield 11 and a housing 12. Compressors 1, 3, 5 and pneumatic turbines 2, 4, 6 are interconnected and mounted on a single shaft 13 in series. The shaft 13, on which compressors and pneumatic turbines are installed, is connected to the shaft 14 of the power turbines 8, 9, having a common combustion chamber 10.

Compressors 1, 3, 5 and pneumatic turbines 2, 4, 6 are enclosed in a jacket 15, forming a cavity 16 between the surfaces of compressors with pneumatic turbines and a jacket, to which the inlet of the heat exchanger 7 is connected, and its output is connected to the multi-tube transition 17, the outputs of which are connected to an annular combustion chamber 10 located between two power turbines 8 and 9.

The combustion chamber 10 is equipped with an annular atomizer 18, which is connected via fuel supply pipes 19 and 20, with an annular fuel evaporator 24, divided into two halves by partitions.

All units are enclosed in the housing 12, while they are separated from it by a heat shield 11 installed between the housing 12 and the jacket 25 of the exhaust cavity 22 (see figure 1).

The operation of the gas turbine installation is as follows.

Air is drawn into the compressor 1 from the environment, where it is partially compressed and fed to the pneumatic turbine 2, in which it partially expands, accompanied by cooling.

Then the air enters the compressor 3, where it is partially compressed by half and enters the pneumatic turbine 4, in which it partially expands, accompanied by cooling.

After that, the air enters the compressor 5, where it is again compressed and fed to the pneumatic turbine 6, in which it partially expands, accompanied by cooling.

Due to the fact that the working pressure in the combustion chamber 10 is lower than the pressure of the compressed air leaving the pneumatic turbine 6, there is a throttling from the cavity 16 to the heat exchanger 7, the outlet of which is connected to the multi-tube transition 17, where its temperature and pressure increase to the maximum allowable maximum.

Then the air enters the annular combustion chamber 10 located between the power turbines 8 and 9.

By means of two pumps (not shown in FIG. 1) operating in parallel, the fuel enters through the fuel supply pipes 19 and 20 and the annular fuel evaporator 24 into the annular atomizer 18, then into the combustion chamber 10.

Moreover, one of the pumps has a higher pressure and works only with afterburner.

After burning fuel in air in the combustion chamber 10, the resulting gas enters the working blades of the power turbines 8 and 9, thereby doing useful work on the shafts 13 and 14.

The exhaust hot gas leaves the power turbines 8, 9, enters the annular space 21, the exhaust cavity 22, gives off heat, heating the air passing through the multi-tube transition 17 to the maximum permissible maximum. The exhaust hot gas simultaneously heats the fuel supply pipelines 19, 20 and the annular fuel evaporator 24. Next, the exhaust gas, bypassing the external plate transition of the heat exchanger 7, enters the environment through the openings 23 in the housing 12.

The heat shield 11 protects the housing 12 from heating, providing a reduction in fire hazard and explosion hazard.

The body of a gas turbine installation for the military industry can be made of modern armor.

The gas turbine unit is supported by three pillow blocks. The support bearing 26 is rigidly connected to the housing 12 through the flange 27 of the multi-tube transition 17 using rods.

Thus, the proposed technical solution allows to increase the efficiency of a gas turbine installation, as well as to increase the reliability and service life of parts operating at high temperatures, while reducing fire hazard and explosion hazard.

In addition, when using the proposed gas turbine installation, vertical take-off of almost all aircraft is possible.

Claims (4)

1. A gas turbine installation comprising a compressor, a pneumatic turbine connected to a compressor shaft, a power turbine, a combustion chamber and a heat exchanger, characterized in that the gas turbine installation further comprises two compressors and two pneumatic turbines, the compressors and pneumatic turbines being interconnected and mounted on in a single shaft in series, while they are enclosed in a jacket, forming a cavity between the surfaces of compressors with pneumatic turbines and the jacket, to which the heat input is connected exchanger, and its output connected to a multi-tubular transition, the outputs of which are connected to an annular combustion chamber, located between the two power turbines. 2. The gas turbine installation according to claim 1, characterized in that the shaft on which the compressors with pneumatic turbines are mounted is connected to the shaft of the power turbines. 3. The gas turbine installation according to claim 1, characterized in that all the units are enclosed in a housing. 4. The gas turbine installation according to claim 1, characterized in that all units enclosed in the housing are separated from it by a heat shield

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