RU2008108083A

RU2008108083A - METHOD AND DEVICE FOR STARTING A GAS-TURBINE UNIT

Info

Publication number: RU2008108083A
Application number: RU2008108083/06A
Authority: RU
Inventors: Дмитрий Александрович Бахтурин (RU); Дмитрий Александрович Бахтурин
Original assignee: Дмитрий Александрович Бахтурин (RU); Дмитрий Александрович Бахтурин
Priority date: 2008-03-04
Filing date: 2008-03-04
Publication date: 2009-09-10
Also published as: RU2374472C1

Abstract

1. Способ пуска газотурбинного агрегата, характеризующийся подачей сжатого газа непосредственно на ротор турбомотора, либо в камеру сгорания, либо тангенциальным способом непосредственно на лопатки ротора, отличающийся тем, что на основной канал подачи воздуха в работающий турбоагрегат (воздухозаборник) устанавливают обратный клапан, а пусковой газ подают непосредственно в камеру сгорания и/или на лопатки ротора турбомашины, причем на период разгона турбоагрегата газ под давлением подают в зону между обратным клапаном и компрессором турбоагрегата. ! 2. Способ пуска газотурбинного агрегата по п.1, отличающийся тем, что устанавливают диффузор с управляемым сечением на выходе из турбины на пути выходящих газов, причем на начальной фазе разгона в диффузоре проходное сечение закрывают до минимального, а по мере разгона ротора диффузор открывают. ! 3. Способ пуска газотурбинного агрегата по п.1 или 2, отличающийся тем, что подаваемый пусковой газ используют как компонент топливной смеси для разгона, розжига, прогрева и принятия турбиной нагрузки. ! 4. Устройство для пуска газотурбинного агрегата, содержащее турбомотор, компрессор, камеру сгорания, воздухозаборник, систему подачи сжатого газа в камеру сгорания, отличающееся тем, что содержит обратный клапан, установленный на воздухозаборнике таким образом, что он пропускает воздушный поток по направлению извне внутрь компрессора, и не допускает обратного движения, когда пусковой газ подается в камеру сгорания, также устройство содержит систему подачи сжатого газа в пространство между обратным клапаном и компрессором. ! 5. Устройство для пуска газотурбинного агрег�1. The method of starting a gas turbine unit, characterized by the supply of compressed gas directly to the rotor of the turbo engine, or to the combustion chamber, or tangentially directly to the rotor blades, characterized in that a check valve is installed on the main air supply channel to the working turbine unit (air intake), and the starting gas is supplied directly to the combustion chamber and / or to the blades of the rotor of the turbomachine, and during the period of acceleration of the turbine unit, gas under pressure is supplied to the zone between the check valve and compressor urban unit. ! 2. The method of starting a gas turbine unit according to claim 1, characterized in that a diffuser with a controlled cross-section is installed at the outlet of the turbine in the path of the exhaust gases, and at the initial phase of acceleration in the diffuser, the passage section is closed to a minimum, and as the rotor accelerates, the diffuser is opened. ! 3. The method of starting a gas turbine unit according to claim 1 or 2, characterized in that the supplied starting gas is used as a component of the fuel mixture for acceleration, ignition, heating and acceptance of the load by the turbine. ! 4. A device for starting a gas turbine unit containing a turbo engine, a compressor, a combustion chamber, an air intake, a compressed gas supply system to the combustion chamber, characterized in that it comprises a check valve mounted on the air intake so that it allows air to flow from the outside into the compressor , and does not allow reverse movement when the starting gas is supplied to the combustion chamber, the device also includes a system for supplying compressed gas to the space between the check valve and the compressor. ! 5. Device for starting a gas turbine unit

Claims

1. The method of starting a gas turbine unit, characterized by the supply of compressed gas directly to the rotor of the turbo engine, or to the combustion chamber, or tangentially directly to the rotor blades, characterized in that a check valve is installed on the main air supply channel to the working turbine unit (air intake), and the starting gas is supplied directly to the combustion chamber and / or to the blades of the rotor of the turbomachine, and during the period of acceleration of the turbine unit, gas under pressure is supplied to the zone between the check valve and compressor urban unit.

2. The method of starting a gas turbine unit according to claim 1, characterized in that a diffuser with a controlled cross-section is installed at the outlet of the turbine in the path of the exhaust gases, and at the initial phase of acceleration in the diffuser, the passage section is closed to a minimum, and as the rotor accelerates, the diffuser is opened.

3. The method of starting a gas turbine unit according to claim 1 or 2, characterized in that the supplied starting gas is used as a component of the fuel mixture for acceleration, ignition, heating and acceptance of the load by the turbine.

4. A device for starting a gas turbine unit containing a turbo engine, a compressor, a combustion chamber, an air intake, a compressed gas supply system to the combustion chamber, characterized in that it comprises a check valve mounted on the air intake so that it allows air to flow from the outside into the compressor , and does not allow reverse movement when the starting gas is supplied to the combustion chamber, the device also includes a system for supplying compressed gas to the space between the check valve and the compressor.

5. The device for starting a gas turbine unit according to claim 4, characterized in that it has a diffuser with a controlled cross-section at the outlet of the turbine in the path of the exhaust gases.