Gas turbine for gas-compressor plant

FIELD: engines and pumps.

SUBSTANCE: proposed gas turbine comprises compressor linked up with the drive. In its turn, compressor drive comprises 1st and 2nd stages, inner and outer shafts with blower fitted on inner shaft and compressor fitted on outer shaft. It includes also HP and LP turbines with cooling system, primary combustion chamber arranged between compressor and HP turbine. Gas turbine comprises also outer combustion chamber and heat exchanger-heater arranged behind HP turbine and communicated, via heat carrier circulation lines, with heat exchanger arranged behind outer combustion chamber.

EFFECT: higher efficiency and reliability.

3 cl, 4 dwg

 

The invention relates to engine, including a powerful stationary gas turbine engines GTD designed primarily for gas pumping units, and can be used for peak power plants as an actuator for an electric generator designed to generate electricity.

Known power plant to a Russian patent for invention №2137617. This unit has a liquid cooling system and a fan for creating a flow of cooling air.

Known power installation according to the patent of Russian Federation №212418, which contains a gas turbine engine, the gas passage connecting this gas turbine engine with a power turbine, and a bypass channel, which connects the gas path between the turbine and before the free turbine.

The disadvantage of this power plant are bad characteristics of its launch, specifically long running times. This is because gas-dynamic resistance of the free turbine is of considerable size, and the capacity of the starter is not sufficient for the simultaneous promotion of several gas turbine engines and the free turbine, which determines the power for the transmission.

Known energy transported gas turbine power plant according to the patent of Russian Federation №2189477, the prototype, which contains the modules gazogenes the Torah, with a compressor, a main combustion chamber and a turbine, gas turbine actuator, and an exhaust system connected.

Disadvantages: low power with a small footprint installation, increased fuel consumption and low reliability due to high temperature before the turbine. More power can be easily achieved with large size, but this will complicate its transportation to remote areas of the country.

Objectives of the invention: increasing capacity, efficiency and reliability of the installation.

These tasks are achieved due to the fact that gas turbine installation for gas pumping units containing a compressor, coupled with a drive that contains, in turn, the first and second paths, the outer and inner shafts with a fan mounted on the inner shaft, and a compressor mounted on the outer shaft, the turbine high and low pressure cooling system, the main combustion chamber between the compressor and the high-pressure turbine, characterized in that it contains an external combustion chamber and heat exchanger-heater installed for the low-pressure turbine connected to the piping of the circulation heat exchanger, set the external combustion chamber. The second circuit has a cooling heat exchanger, the input is connected to the compressor outlet, and the output from the cooling turbine. The external combustion chamber connected to the gas main through the valve and the regulator, and the main combustion chamber through the valve, the booster compressor and the controller.

For the implementation of the invention rather use a well-known units and components, previously developed and implemented in the design of gas turbine engines and in mechanical engineering.

The invention is illustrated in figure 1...4, where:

figure 1 shows the first variant of the engine,

figure 2 shows a second variant of the engine,

figure 3 shows a cooling system of the turbine,

figure 4 shows the section a-A.

The proposed technical solution (figure 1) contains a gas compressor 1 and the actuator 2. The actuator 2 is made on the basis of gas turbine engine and includes two circuits: the first 3 and second 4, respectively, two shaft: inner 5 and outer 6, i.e. the actuator 2 is made of double-circuit on double-shaft scheme. In addition, the actuator 2 includes an inlet 7, the fan 8, the compressor 9, the main combustion chamber 10 and the turbine 11. Turbine 11 includes a high-pressure turbine 12 and a low-pressure turbine 13. Each of the turbines 12 and 13 can have either one or several stages. In the future, consider an example with a single-stage turbines. High pressure turbine 12 includes first to allow the apparatus of the turbine 14 and the first work is olaso turbine 15, and the level of the low-pressure turbine 13 - second to allow the apparatus of the turbine 16 and the second turbine wheel 17. The first turbine wheel 15 mounted on the outer shaft 6 and the second turbine wheel 17 on the inner shaft 3. The output of both circuits 3 and 4 are jet nozzle 18.

Outside drive 2 installed external combustion chamber 19 to the nozzle 20 and the heat exchanger 21 at the outlet and the exhaust device 22 after the heat exchanger 21. Between the turbines of high and low pressure 12 and 13 has a heat exchanger-heater 23.

The heat exchanger 21 is connected by piping recirculation of the fluid, respectively, the inlet 24 and outlet 25 with heat exchanger-heater 23. Between the heat exchanger 21 and the inlet of the recirculation pipe of the heat carrier 24 has a pump fluid 26 to the actuator 27, and the discharge pipe recirculation coolant 25 connects the heat exchanger-heater 23 to the heat exchanger 21 to drain the coolant. The coolant, it is preferable to use liquid sodium.

Gas turbine plant comprises two fuel injection system 28 and 29 fuel (natural gas) in the main combustion chamber 10 and the external combustion chamber 21. Both handling system connected to the gas line 30. The main fuel injection system 28 includes a base is obliverated 31, connected to the gas line 30 containing valve 32 and the regulator 33, and its output is connected with the annular manifold 34. The annular manifold 34 is connected to the nozzles 35 of the main combustion chamber 10.

Additional fuel injection system 29 includes an additional fuel line 36 from the controller 37, which is connected to the nozzle 20. To the external combustion chamber 19 is connected an air pipe 38 with an airflow switch 39. The unit has a control unit 40, connected to the electrical connections with the valve 32 and regulators 33, 37 and 39.

The compressor 9 contains the compressor rotor 41 with the outer shaft 6. On the outer shaft 6 is also installed the first turbine wheel 15.

In the second circuit 4 (figure 2) can be installed cooling heat exchanger 42, the inlet of which is connected by a pipe air sampling 43 with the output of the compressor 7, and the output of the supply pipe 44 with the cooling system 45 of the turbine 11 (turbines 12 and 13).

Cooling system 45 of the turbine 11 (3 and 4) contains the header 46, mounted above the first nozzle device 14, and the cooling system high-pressure turbine, containing, in turn, the diaphragm 47 is connected through the first to allow the device 14 to the motor housing 48, the deflector 49, mounted on the turbine disk 50 and the seal 51. Cooling system turbine 45 is insulated from the heat exchanger - heating the El 23 insulating partition wall 52. First to allow the device 14 and the first turbine wheel 15 are hollow cooled blade. Between the inner shaft 5 and the insulating partition wall 52 is formed an annular channel B for the passage of cooling air from the high-pressure turbine 14 to the low pressure turbine 13. Similarly, the cooling system high-pressure turbine 12 is made cooling system low-pressure turbine 13 (Fig 3 and 4).

Heat exchangers-heaters 23 mounted on the insulating partition 52, within which the collector of the carrier 53, for the distribution of coolant (liquid sodium) elements 54 of the heat exchanger-heater 23 (Fig 3 and 4). To the collector of the carrier 53 docked supply line of the circulation of the coolant 24.

When working GTE carry it to run the starter (starter 1...3 not shown). When this spin only one rotor of the two. At the same time on command from the control unit 40 opens the valve 32, and the fuel is injected into the main combustion chamber 10 to the nozzles 35, where it is ignited by electrocapillary (figure 1...4 not shown), and the nozzles 20 of the outer combustion chamber 19.

As a result, the combustion products pass through the impellers of the turbine 15 and 17 and untwist them, as well as the outer shaft 6 and the inner shaft 5. The heat removed in the heat exchanger 21 via the heat is osites, supplied through the supply line recirculation of the coolant 24, heats the heat exchanger-heater 23, which heats, in turn, the products of combustion for the first the high-pressure turbine 12, which improves the capacity and efficiency of the entire installation.

The application of the invention allowed:

1. To improve the starting and acceleration of the actuator installation on transient conditions, due to the use of cheap fuel (natural gas) and heat generated in an external combustion chamber at the same time.

2. To increase the reliability of the engine

- due to the fact that the failure of one of the fuel system it can a long time to work in 50% of nominal,

due to the application of an effective system cooling turbine, and a cooling heat exchanger.

3. To improve plant efficiency due to a more rational layout of the drive and no hard kinematic connection between the two shafts. This allowed us to design the optimal compressor and turbine.

4. To improve reliability by reducing the number of turbine stages to the same degree and distribution of the greater part of the load on the second and subsequent stage of the turbine, if any.

5. To create favorable conditions for the operation of the fan, compressor, coordinating optimal estimated angular velocity of rotation of the vent is the system. The use of twin-shaft scheme engine to drive will allow you to unleash mechanical impellers and rotors of turbines and compressors.

6. To ensure optimum operation of the drive motor at the transient modes.

7. Significantly reduce the specific fuel consumption during operation of the installation.

8. To facilitate the working conditions of the fan due to its rigid connection with the shaft of the compressor and the possibility of their mutual slippage and misalignment of the rotor of the compressor and the rotor of the fan.

9. To facilitate the starting and stopping of the drive of the installation due to the use of twin-shaft schema.

10. To reduce the size and weight and the total weight of the installation due to compact

11. To reduce installation costs by eliminating expensive materials used in the manufacture of the turbine, and to solve the problem of cooling the turbine, first, reducing the temperature before it, and secondly, sending the entire cooling air for cooling only one or two turbine stages, instead of 4...5 speed manual, used previously on powerful gas turbine engines.

1. Gas turbine installation for gas pumping units containing a compressor, coupled with a drive that contains in turn the first and second paths, the outer and inner shafts with a fan mounted on the inner shaft and the compressor mounted on the current shaft, turbine high and low pressure cooling system, the main combustion chamber between the compressor and the high-pressure turbine, characterized in that it contains an external combustion chamber and heat exchanger-heater installed for the high-pressure turbine connected to the piping of the circulation heat exchanger mounted outside the combustion chamber.

2. Gas turbine installation according to claim 1, characterized in that the second circuit has a cooling heat exchanger, the inlet of which is connected to the output of the compressor, and the output from the cooling turbine.

3. Gas turbine installation according to claim 1 or 2, characterized in that the external combustion chamber connected to the gas main through the valve and the regulator, and the main combustion chamber through the valve, booster compressor and regulator.



 

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