EP0259758A2
Expired / Lapsed
EP
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Method for controlling a catalytic combustor of a gas turbine
Assignee: Hitachi Ltd
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Filing: 1987-09-01
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Granted: —
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Expires: 2007-09-01
Abstract
Abstract A catalytic combustor for a gas turbine comprises catalyst layers (l, 2) arranged in two stages in a direction of gas flow. Fuel supply nozzles are (4,5) disposed close to and upstream of the downstream catalyst layer (l,2). A substantially constant amount of fuel is supplied from the fuel supply nozzles (4,5,6,7) to form pilot flames by the downstream catalyst layer (2), which are above l000 degrees C and below l500 degrees C. Combustible component having passed through the upstream catalyst layer (l) is burned by the pilot flames.
Inventors
- 👤 Kazumi Iwai
- 👤 Hiromi Koizumi
- 👤 Katsuo Wada
Bibliographic Details
Application Number
—
Jurisdiction
EP
Data Source
google_patents
Last Synchronized
2026-10-26 00:47
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/40
Claims Analysis
Total Claims: 5
Claim 1
Independent Claim
114 words
A catalytic combustor for a gas turbine, comprising: a plurality of stages of catalyst layers (l, 2) arranged in a direction of gas flow; a plurality of fuel supply nozzles, (4, 5, 6, 7) disposed upstream of each of said catalyst layers; (l, 2) and means for controlling flow rate of fuel from said fuel supply nozzles (4,5) disposed close to and upstream of the last stage catalyst layer (2) in the direction of gas flow, to a substantially constant value regardless of load on the turbine, wherein pilot flames can be formed at a location including said last stage catalyst layer (2) and close to and including said last stage catalyst layer (2).
Claim 2
Dependent Claim
114 words
A catalytic combustor for a gas turbine, comprising: a plurality of stages of catalyst layers (l, 2) arranged in a direction of gas flow; a plurality of fuel supply nozzles, (4, 5, 6, 7) disposed upstream of each of said catalyst layers; (l, 2) and means for controlling flow rate of fuel from said fuel supply nozzles (4,5) disposed close to and upstream of the last stage catalyst layer (2) in the direction of gas flow, to a substantially constant value regardless of load on the turbine, wherein pilot flames can be formed at a location including said last stage catalyst layer (2) and close to and including said last stage catalyst layer (2).
Claim 3
Dependent Claim
24 words
A catalytic combustor as defined in Claim l, wherein a diffusion combustion nozzle is further provided upstream of the first stage catalyst layer (l).
Claim 4
Dependent Claim
41 words
A catalytic combustor as defined in Claim l, wherein fuel concentration is so set that the pilot flames formed at the last stage catalyst layer (2) is brought to a temperature level above l000 degrees C and below l500 degrees C.
Claim 5
Dependent Claim
37 words
A catalytic combustor as defined in Claim l, wherein the last stage catalyst layer (2) employs catalyst higher in heat resistant temperature than that of the catalyst layer (l) upstream of said last stage catalyst layer (2).
References Cited (Backward Citations)
No citation records indexed.
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