[특허]Process for cooling the turbine stage and gas turbine having a cooled turbine stage

SIEMENS AKTIENGESELLSCHAFT

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특허 상세정보

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Process for cooling the turbine stage and gas turbine having a cooled turbine stage

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-025/12 F01D-005/18 F02C-007/18
출원번호	US-0009905 (2012-03-08)
등록번호	US-10180081 (2019-01-15)
우선권정보	EP-11161499 (2011-04-07)
국제출원번호	PCT/EP2012/053971 (2012-03-08)
§371/§102 date	20131209 (20131209)
국제공개번호	WO2012/136437 (2012-10-11)
발명자 / 주소	Bolms, Hans-Thomas Dobrzynski, Boris
출원인 / 주소	SIEMENS AKTIENGESELLSCHAFT
인용정보	피인용 횟수 : 0 인용 특허 : 2

초록
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A gas turbine having a turbine stage is presented. The gas turbine has a guide vane that can be operated cooled by a cooling medium, and a cooling medium feed device for feeding the cooling medium into the interior of the guide van, which, in the region of its rear edge, has on the pressure side at least one cooling medium outlet opening, through which the cooling medium can flow out of the interior of the guide vane into the main flow. The cooling medium feed device has a mass flow control device for controlling the mass flow through the at least one co...

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1. A method for cooling a turbine stage of a gas turbine, wherein the turbine stage comprises a guide blade that is operable with cooling by a cooling medium, the method comprising: operating the gas turbine at part load;supplying the cooling medium into an interior of the guide blade by a cooling medium supply device, wherein the guide blade in a region of a trailing edge and on a pressure side comprises at least one cooling medium outlet opening through which the cooling medium can be caused to flow out of the interior of the guide blade into a main flow, and wherein the cooling medium supply device comprises a bleed line, a mass flow control device, a supply line, a cooling air reservoir, a cooling air inlet, and a chamber; andcontrolling the mass flow control device such that a mass flow of the cooling medium flowing via the chamber into the interior of the guide blade is increased at the part load operation in relation to the mass flow of the cooling medium flowing via the chamber into the interior of the guide blade at full-load operation of the gas turbine,wherein the mass flow control device comprises a throttle valve,wherein the bleed line is connected to a compressor plenum and merges via the throttle valve into the supply line, the supply line issues into the cooling air reservoir, cooling air reservoir is bridged with the chamber via the cooling air inlet,wherein the bleed line bleeds compressor air in the compressor plenum as the cooling medium,wherein an amount of the cooling medium in the compressor plenum in the part load operation is greater than an amount of the cooling medium in the compressor plenum in the full-load operation,wherein the throttle valve is placed into a throttling position at the full-load operation such that the mass flow of the cooling medium flowing via the chamber into the interior of the guide blade is reduced for cooling the guide blade, andwherein the throttle valve is opened at the part load operation such that the mass flow of the cooling medium flowing via the chamber into the interior of the guide blade is increased by bleeding the greater amount of the cooling medium in the compressor plenum in the part load operation for cooling the guide blade and adjusting a diversion angle of the guide blade. 2. The method as claimed in claim 1, wherein the guide blade is designed for the mass flow of the cooling medium which is not throttled by the throttle valve in the part load operation. 3. The method as claimed in claim 1, wherein the bleed line bleeds compressor exit air as the cooling medium and the mass flow control device is fed with the compressor exit air from the compressor exit. 4. The method as claimed in claim 3, wherein in the part load operation of the gas turbine, the compressor exit air is conducted so as to bypass a combustion chamber of the gas turbine. 5. The method as claimed in claim 1, wherein the cooling medium is provided to the cooling medium inlet from the cooling medium reservoir by the mass flow control device. 6. The method as claimed in claim 1, wherein the mass flow control device is fed from a compressor plenum of the gas turbine. 7. The method as claimed in claim 1, wherein the guide blade is a first guide blade arranged immediately downstream of a combustion chamber of the gas turbine of a first turbine stage of the gas turbine. 8. The method as claimed in claim 1, wherein the mass flow is set such that the part load operation of the gas turbine is optimized with regard to a thermodynamic efficiency, and/or with regard to a flow impingement angle on a rotor blade arranged downstream of the guide blade, and/or with regard to an exhaust-gas temperature of the turbine of the gas turbine, and/or with regard to a flame stability in the combustion chamber of the gas turbine. 9. A method for operating a gas turbine comprising a turbine stage, wherein the turbine stage comprises a guide blade that is cooled by a cooling medium the method comprising: supplying the cooling medium into an interior of the guide blade by a cooling medium supply device, wherein the guide blade, in an outer surface, comprises multiple cooling medium outlet openings through which the cooling medium can be caused to flow out of the interior of the guide blade into a main flow, and wherein the cooling medium supply device comprises a bleed line, a mass flow control device, a supply line, a cooling air reservoir, a cooling air inlet, and a chamber;controlling a mass flow of the cooling medium flowing via the chamber into the interior of the guide blade by the mass flow control device during operation of the gas turbine; andincreasing the mass flow of the cooling medium flowing via the chamber into the interior of the guide blade with a reduction in gas turbine power,wherein the mass flow control device comprises a throttle valve,wherein the bleed line is connected to a compressor plenum and merges via the throttle valve into the supply line, the supply line issues into the cooling air reservoir, cooling air reservoir is bridged with the chamber via the cooling air inlet,wherein the bleed line bleeds compressor air in the compressor plenum as the cooling medium,wherein an amount of the cooling medium in the compressor plenum in a part load operation is greater than an amount of the cooling medium in the compressor plenum in a full-load operation,wherein the throttle valve is placed into a throttling position at the full-load operation such that the mass flow of the cooling medium flowing via the chamber into the interior of the guide blade is reduced for cooling the guide blade, andwherein the throttle valve is opened at the part load operation such that the mass flow of the cooling medium flowing via the chamber into the interior of the guide blade is increased by bleeding the greater amount of the cooling medium in the compressor plenum in the part load operation for cooling the guide blade and adjusting a diversion angle of the guide blade. 10. A gas turbine, comprising: a turbine stage;a guide blade;at least one cooling medium outlet opening arranged in a region of a trailing edge and on a pressure side of the guide blade through which a cooling medium can be caused to flow out of an interior of the guide blade into a main flow; anda cooling medium supply device for supplying the cooling medium via a cooling air inlet into the interior of the guide blade, wherein the cooling medium supply device comprises a bleed line, a mass flow control device, a supply line, a cooling air reservoir, a cooling air inlet, and a chamber,wherein the mass flow control device controls a mass flow of the cooling medium flowing via the chamber into the interior of the guide blade such that the mass flow of the cooling medium flowing via the chamber into the guide blade is increased at part load operation of the gas turbine in relation to the mass flow of the cooling medium flowing via the chamber into the interior of the guide blade at full-load operation of the gas turbine,wherein the mass flow control device comprises a throttle valve,wherein the bleed line is connected to a compressor plenum and merges via the throttle valve into the supply line, the supply line issues into the cooling air reservoir, cooling air reservoir is bridged with the chamber via the cooling air inlet,wherein the bleed line bleeds compressor air in the compressor plenum as the cooling medium,wherein an amount of the cooling medium in the compressor plenum in the part load operation is greater than an amount of the cooling medium in the compressor plenum in the full-load operation,wherein the throttle valve is placed into a throttling position at the full-load operation such that the mass flow of the cooling medium flowing via the chamber into the interior of the guide blade is reduced for cooling the guide blade, andwherein the throttle valve is opened at the part load operation such that the mass flow of the cooling medium flowing via the chamber into the interior of the guide blade is increased by bleeding the greater amount of the cooling medium in the compressor plenum in the part load operation for cooling the guide blade and adjusting a diversion angle of the guide blade.

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Process for cooling the turbine stage and gas turbine having a cooled turbine stage

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Process for cooling the turbine stage and gas turbine having a cooled turbine stage

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