RU96117119A - COMBUSTION CHAMBER FOR GAS TURBINE - Google Patents

COMBUSTION CHAMBER FOR GAS TURBINE

Info

Publication number
RU96117119A
RU96117119A RU96117119/06A RU96117119A RU96117119A RU 96117119 A RU96117119 A RU 96117119A RU 96117119/06 A RU96117119/06 A RU 96117119/06A RU 96117119 A RU96117119 A RU 96117119A RU 96117119 A RU96117119 A RU 96117119A
Authority
RU
Russia
Prior art keywords
combustion chamber
chamber according
stream
inlet
ribs
Prior art date
Application number
RU96117119/06A
Other languages
Russian (ru)
Other versions
RU2133916C1 (en
Inventor
Магхон Хельмут
Original Assignee
Сименс АГ
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Сименс АГ filed Critical Сименс АГ
Priority claimed from PCT/EP1995/000245 external-priority patent/WO1995020130A1/en
Publication of RU96117119A publication Critical patent/RU96117119A/en
Application granted granted Critical
Publication of RU2133916C1 publication Critical patent/RU2133916C1/en

Links

Claims (7)

1. Камера сгорания для газовой турбины, которая вдоль оси является протекаемой текущим из компрессорной части к турбинной части, поступающим на входе и имеющим завихрение потоком сжатого воздуха, содержащая расположенный на входе кольцевой канал с расположенной в нем впускной частью для отделения из потока частичного потока, причем впускная часть сообщается с пилотными горелками для стабилизации горения в камере сгорания, отличающаяся тем, что впускная часть содержит средства для устранения из частичного потока его завихрения и дополнительно сообщается с каналами охлаждения для охлаждения камеры сгорания.1. The combustion chamber for a gas turbine, which is flowing along the axis flowing from the compressor part to the turbine part, coming in at the inlet and having a swirling stream of compressed air, containing an annular channel located at the inlet with an inlet part located therein to separate a partial stream from the stream, moreover, the inlet part communicates with the pilot burners to stabilize combustion in the combustion chamber, characterized in that the inlet part contains means for eliminating from a partial stream of its swirl and tion communicates with cooling passages for cooling the combustion chamber. 2. Камера сгорания по п. 1, отличающаяся тем, что впускная часть простирается через имеющую кольцевую форму частичную область кольцевого канала и соединена трубами с каналами охлаждения. 2. The combustion chamber according to claim 1, characterized in that the inlet part extends through a ring-shaped partial region of the annular channel and is connected by pipes to the cooling channels. 3. Камера сгорания по п. 1 или 2, отличающаяся тем, что средства для устранения из частичного потока его завихрения выполнены в виде направляющих лопаток. 3. The combustion chamber according to claim 1 or 2, characterized in that the means for eliminating the turbulence from the partial flow thereof are made in the form of guide vanes. 4. Камера сгорания по одному из предыдущих пунктов, отличающаяся тем, что она имеет ребра для подвода топлива к потоку, причем топливо воспламеняется и сгорает на пилотном пламени, поставляемом пилотными горелками, а также систему подачи топлива для подвода топлива, как к пилотным горелкам, так и к ребрам. 4. The combustion chamber according to one of the preceding paragraphs, characterized in that it has fins for supplying fuel to the stream, and the fuel is ignited and burns on the pilot flame supplied by the pilot burners, as well as a fuel supply system for supplying fuel, as to pilot burners, so to the ribs. 5. Камера сгорания по п. 4, отличающаяся тем, что пилотные горелки имеются предпочтительно в таком количестве, которое соответствует половинному или целому количеству, в котором имеются ребра. 5. The combustion chamber according to claim 4, characterized in that the pilot burners are preferably in an amount that corresponds to half or the whole amount in which there are fins. 6. Камера сгорания по п. 5, отличающаяся тем, что она подключена к турбинной части, обтекаемой потоком через венец направляющих лопаток, причем количество ребер равно количеству направляющих лопаток. 6. The combustion chamber according to claim 5, characterized in that it is connected to the turbine part streamlined through the crown of guide vanes, the number of ribs being equal to the number of guide vanes. 7. Камера сгорания по одному из пп. 4 - 6, отличающаяся тем, что после кольцевого канала встроены только ребра. 7. The combustion chamber according to one of paragraphs. 4 - 6, characterized in that after the annular channel only ribs are integrated.
RU96117119A 1994-01-24 1995-01-24 Gas turbine combustion chamber RU2133916C1 (en)

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
EP94100989 1994-01-24
EP94100988.8 1994-01-24
EP94100989.6 1994-01-24
EP94100988 1994-01-24
PCT/EP1995/000245 WO1995020130A1 (en) 1994-01-24 1995-01-24 Combustion chamber for a gas turbine

Publications (2)

Publication Number Publication Date
RU96117119A true RU96117119A (en) 1998-11-20
RU2133916C1 RU2133916C1 (en) 1999-07-27

Family

ID=26135445

Family Applications (2)

Application Number Title Priority Date Filing Date
RU96117120A RU2142601C1 (en) 1994-01-24 1995-01-24 Method for fuel combustion in compressed air
RU96117119A RU2133916C1 (en) 1994-01-24 1995-01-24 Gas turbine combustion chamber

Family Applications Before (1)

Application Number Title Priority Date Filing Date
RU96117120A RU2142601C1 (en) 1994-01-24 1995-01-24 Method for fuel combustion in compressed air

Country Status (10)

Country Link
US (1) US5735115A (en)
EP (2) EP0741850B1 (en)
JP (2) JPH09507703A (en)
KR (2) KR970700846A (en)
CN (2) CN1140489A (en)
CZ (2) CZ217496A3 (en)
DE (2) DE59502335D1 (en)
ES (2) ES2117402T3 (en)
RU (2) RU2142601C1 (en)
WO (2) WO1995020131A1 (en)

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