RU96117120A - METHOD FOR COMBUSING FUEL IN COMPRESSED AIR - Google Patents

METHOD FOR COMBUSING FUEL IN COMPRESSED AIR

Info

Publication number
RU96117120A
RU96117120A RU96117120/06A RU96117120A RU96117120A RU 96117120 A RU96117120 A RU 96117120A RU 96117120/06 A RU96117120/06 A RU 96117120/06A RU 96117120 A RU96117120 A RU 96117120A RU 96117120 A RU96117120 A RU 96117120A
Authority
RU
Russia
Prior art keywords
stream
fuel
partial streams
supplied
compressed air
Prior art date
Application number
RU96117120/06A
Other languages
Russian (ru)
Other versions
RU2142601C1 (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/EP1995/000244 external-priority patent/WO1995020131A1/en
Publication of RU96117120A publication Critical patent/RU96117120A/en
Application granted granted Critical
Publication of RU2142601C1 publication Critical patent/RU2142601C1/en

Links

Claims (5)

1. Способ сжигания топлива в сжатом воздухе, который подают в перемещающемся вдоль оси (1) потоке (2), при котором вначале от потока (2) отделяют множество частичных потоков (3), к каждому из которых по отдельности подводят часть топлива и сжигают во вдающемся в поток (2) пилотном пламени (25), и при котором остальное топливо распределяют в потоке (2), поджигают на пилотных пламенях (25) и сжигают, отличающийся тем, что остальное топливо распределяют в потоке (2) неоднородно, причем образующееся за счет этого распределение (28) топлива в потоке (2) имеет локальный максимум (29) на каждом пилотном пламени (25).1. A method of burning fuel in compressed air, which is supplied in a stream (2) moving along the axis (1), in which at the beginning, many partial streams (3) are separated from the stream (2), each of which is separately supplied with a portion of the fuel and burned in a pilot flame (25) projecting into the stream (2), and in which the rest of the fuel is distributed in the stream (2), ignited on the pilot flames (25) and burned, characterized in that the remaining fuel is distributed non-uniformly in the stream (2), moreover the distribution of fuel (28) formed in this way in the stream (2) has a lock The maximum (29) at each pilot flame (25). 2. Способ по п.1, при котором поток (2) имеет завихрение относительно оси (1). 2. The method according to claim 1, wherein the stream (2) has a swirl relative to the axis (1). 3. Способ по п.2, при котором от части потока (2), из которого ответвляют частичные потоки (3), перед ответвлением частичных потоков (3) устраняют завихрение. 3. The method according to claim 2, in which the turbulence is eliminated from the part of the stream (2) from which the partial streams (3) branch, before the branch of the partial streams (3). 4. Способ по одному из предыдущих пунктов, при котором поток (2) подают из компрессорной части (4) газовой турбины и после сжигания топлива подводят к турбинной части (5) газовой турбины. 4. The method according to one of the preceding paragraphs, in which the stream (2) is supplied from the compressor part (4) of the gas turbine and, after burning the fuel, is led to the turbine part (5) of the gas turbine. 5. Способ по п.4, при котором поток (2) притекает к турбинной части (5) через входной зазор (14), в котором расположены направляющие лопатки (15) и причем за счет сжигания топлива в потоке (2) возникает неоднородное распределение температуры, имеющее локальные максимумы, каждый из которых лежит между двумя направляющими лопатками (15). 5. The method according to claim 4, in which the stream (2) flows to the turbine part (5) through the inlet gap (14), in which the guide vanes (15) are located, and moreover, an inhomogeneous distribution occurs in the stream (2) due to fuel combustion temperature, having local maxima, each of which lies between two guide vanes (15).
RU96117120A 1994-01-24 1995-01-24 Method for fuel combustion in compressed air RU2142601C1 (en)

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
EP94100988 1994-01-24
EP94100988.8 1994-01-24
EP94100989.6 1994-01-24
EP94100989 1994-01-24
PCT/EP1995/000244 WO1995020131A1 (en) 1994-01-24 1995-01-24 Method of burning fuel in compressed air

Publications (2)

Publication Number Publication Date
RU96117120A true RU96117120A (en) 1998-11-27
RU2142601C1 RU2142601C1 (en) 1999-12-10

Family

ID=26135445

Family Applications (2)

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

Family Applications Before (1)

Application Number Title Priority Date Filing Date
RU96117119A RU2133916C1 (en) 1994-01-24 1995-01-24 Gas turbine combustion chamber

Country Status (10)

Country Link
US (1) US5735115A (en)
EP (2) EP0741849B1 (en)
JP (2) JP3667757B2 (en)
KR (2) KR970700846A (en)
CN (2) CN1140489A (en)
CZ (2) CZ217496A3 (en)
DE (2) DE59502335D1 (en)
ES (2) ES2126881T3 (en)
RU (2) RU2133916C1 (en)
WO (2) WO1995020130A1 (en)

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