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CN-224228754-U - Fuel system of gas turbine and gas turbine

CN224228754UCN 224228754 UCN224228754 UCN 224228754UCN-224228754-U

Abstract

The application discloses a fuel system of a gas turbine and the gas turbine, which belong to the technical field of gas turbines, and comprise an ignition oil way, a working oil way and a return oil way, wherein the ignition oil way is used for communicating a fuel tank with an ignition nozzle of the gas turbine; the working oil way is used for communicating the fuel tank with a working nozzle of the gas turbine, the fuel tank is connected with the main fuel pump through the auxiliary fuel pump, the outlet of the main fuel pump is connected to the inlet of the fuel regulating valve, the bypass port of the fuel regulating valve is connected to the front end of the main fuel pump, the quick cut-off valve is used for cutting off the working oil way, the inlet of the return exhaust oil way is connected with the oil way between the fuel regulating valve and the quick cut-off valve, and the outlet of the return exhaust oil way is connected with the fuel tank. According to the application, the industrial type combustion regulating valve is adopted to reduce the cost and the purchasing period, and the quick cut-off valve is arranged at the same time, so that the quick cut-off of an oil way can be realized during emergency shutdown, and the phenomena of substandard exhaust emission and the like are avoided.

Inventors

  • WANG MIN
  • LIU CHAO
  • Tan Zhishuai
  • XU HONG
  • SHEN SHIDONG
  • WEI BINGXIA

Assignees

  • 航发燃机(株洲)有限公司

Dates

Publication Date
20260512
Application Date
20250606

Claims (10)

  1. 1. The fuel system of the gas turbine is characterized by comprising a fuel tank (300), an ignition oil path, a working oil path and a return oil path, wherein the ignition oil path is used for communicating the fuel tank (300) with an ignition nozzle (900) of the gas turbine, an electric pump (1200) and an ignition electromagnetic valve (1300) are sequentially arranged on the ignition oil path, the ignition oil path is communicated with the working oil path, the working oil path is used for communicating the fuel tank (300) with the working nozzle (1000) of the gas turbine, an auxiliary fuel pump (200), a main fuel pump (100), a fuel regulating valve (500) and a quick cut-off valve (600) are sequentially arranged on the working oil path, a bypass port of the fuel regulating valve (500) is connected to the front end of the main fuel pump (100), the quick cut-off valve (600) is used for cutting off the working oil path, an inlet of the return oil path is connected with an oil path between the fuel regulating valve (500) and the quick cut-off valve (600), and an outlet of the return oil path is connected with the fuel tank (300).
  2. 2. The fuel system of a gas turbine according to claim 1, characterized in that the first outlet of the auxiliary fuel pump (200) is connected to the main fuel pump (100), the branch of the electric pump (1200) is connected to the second outlet of the auxiliary fuel pump (200), and that a one-way valve is arranged in the branch of the electric pump (1200), the main fuel pump outlet is connected to the pilot valve inlet, and the bypass port of the pilot valve (500) is connected to the main fuel pump inlet.
  3. 3. The fuel system of a gas turbine according to claim 2, characterized in that the fuel system of the gas turbine further comprises a blow-down oil circuit for connecting a gas turbine blow-down outlet (1100) of the gas turbine with a blow-down tank (800), the third outlet of the auxiliary fuel pump (200) being further connected with the blow-down oil circuit.
  4. 4. The fuel system of a gas turbine according to claim 1, further comprising a fuel filter (400), the fuel filter (400) being arranged between the main fuel pump (100) and the pilot valve (500).
  5. 5. The fuel system of a gas turbine according to claim 4, characterized in that a first pressure sensor, a first flow sensor and a first temperature sensor are arranged between the fuel filter (400) and the combustion valve (500).
  6. 6. A gas turbine fuel system according to claim 1, characterized in that a second pressure sensor, a second flow sensor and a second temperature sensor are arranged between the quick shut-off valve (600) and the working nozzle (1000).
  7. 7. A gas turbine fuel system according to claim 1, characterized in that the return oil circuit is provided with a discharge valve (700).
  8. 8. A gas turbine fuel system according to claim 7, characterized in that the discharge valve (700) is a fail-open type.
  9. 9. The fuel system of a gas turbine according to claim 1, wherein said electric pump (1200) is a dc electric pump.
  10. 10. A gas turbine comprising a fuel system of a gas turbine according to any one of claims 1-9.

Description

Fuel system of gas turbine and gas turbine Technical Field The application relates to the technical field of gas turbines, in particular to a fuel system of a gas turbine and the gas turbine. The application also relates to a gas turbine comprising the fuel system of the gas turbine. Background The information provided in this section is for the purpose of generally presenting the context of the disclosure. Work of the presently named inventors, to the extent it is described in this section, as well as aspects of the description that may not otherwise qualify as prior art at the time of filing, are neither expressly nor impliedly admitted as prior art against the present disclosure. The current fuel system applied to the gas turbine generator set is usually that fuel oil is connected to a main fuel pump from an electric booster pump to an auxiliary fuel pump and one way of an outlet of the auxiliary fuel pump, high-pressure fuel oil of the main fuel pump enters a fuel regulating valve, the fuel regulating valve is a gas turbine self-contained device, the fuel regulating valve belongs to special equipment of an engine, fuel oil at the outlet of the fuel regulating valve enters the gas turbine, a bypass port of the fuel regulating valve is connected to the front of the main fuel pump, the other way of the auxiliary fuel pump is connected to a starting valve of the fuel turbine, and the valve is the gas turbine self-contained device and belongs to special equipment of the engine. The liquid fuel system, the control method, the medium and the equipment of the gas turbine disclosed in China patent publication No. CN117738796A comprise a fuel tank, a main oil way, a surge oil way, a mixed oil way and a liquid fuel annular main pipe, wherein an inlet of the main oil way is communicated with the fuel tank, an outlet of the main oil way is communicated with an inlet of the mixed oil way, an inlet of the surge oil way is communicated with the fuel tank, an outlet of the surge oil way is communicated with an inlet of the mixed oil way, a booster pump is arranged in the surge oil way, and an outlet of the mixed oil way is communicated with an inlet of the annular main pipe. According to the scheme, the main oil way and the surge oil way are arranged, the booster pump is arranged in the surge oil way, and when the gas turbine is started and the gas fuel is switched to the liquid fuel, the main oil way and the surge oil way are used for supplying oil to the liquid fuel annular main pipe, so that the time for filling the liquid fuel into the liquid fuel annular main pipe can be shortened, and the time difference of spraying the liquid fuel by each nozzle is reduced. The existing fuel oil system still has the following defects that 1, the flow of an electric booster pump needs to meet the system requirement, a motor is generally alternating current, the electric booster pump is not suitable for an emergency unit, the emergency unit does not have alternating current supply, 2, a combustion regulating valve and a starting valve are special equipment of an engine, the purchasing period is long, the price is high, the market competitiveness of the civil combustion engine unit is lacking, the primary combustion regulating valve is inconvenient to realize automatic control, and 3, when the system is in emergency stop, the oil way is not cut off rapidly enough, so that the tail gas emission does not reach the standard. Disclosure of utility model In view of at least one of the above technical problems, the application provides a fuel system of a gas turbine, which can reduce cost and purchasing period by adopting an industrial type fuel regulating valve, and simultaneously, a quick cut-off valve is arranged, so that quick cut-off of an oil way can be realized during emergency shutdown, and the phenomena of substandard exhaust emission and the like are avoided. The application also provides a gas turbine comprising the fuel system of the gas turbine. According to one aspect of the application, a fuel system of a gas turbine is provided, and the fuel system comprises a fuel tank, an ignition oil way, a working oil way and a return oil way, wherein the ignition oil way is used for communicating the fuel tank with an ignition nozzle of the gas turbine, an electric pump and an ignition electromagnetic valve are sequentially arranged on the ignition oil way, the ignition oil way is communicated with the working oil way, the working oil way is used for communicating the fuel tank with the working nozzle of the gas turbine, an auxiliary fuel pump, a main fuel pump, a fuel regulating valve and a quick cut-off valve are sequentially arranged on the working oil way, a bypass port of the fuel regulating valve is connected to the front end of the main fuel pump, the quick cut-off valve is used for cutting off the working oil way, an inlet of the return oil way is connected with an oil way between the fuel regulating valve and the quick cut-of