US4112675A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Apparatus and method for starting a large gas turbine having a catalytic combustor
Assignee: Westinghouse Electric Corp
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Filing: 1976-09-30
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Granted: 1978-09-12
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Expires: 1996-09-30
Abstract
Abstract Apparatus and method for starting a gas turbine engine is shown wherein the combustion chamber has a fixed geometry providing a high throughput velocity to prevent flashback during normal operation of the engine. Thus, there is provided a flame holding zone out of the main flow path through the chamber that exhausts into the chamber upstream of a catalytic reactor element to preheat the catalyst to a sufficiently high temperature for continuous auto-combustion therein prior to the rotor of the engine attaining running speed. After running speed the combustion in the flame holding zone is extinguished and the velocity of the fuel/air mixture in the main flow path through the chamber is sufficient to maintain the combustion within the catalytic element for the continuous running of the engine without any flashback.
Inventors
- 👤 Paul W. Pillsbury
- 👤 Serafino M. DeCorso
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-27 05:22
CPC Classifications
F; F02; F02C; F02C7/00; F02C7/26; F23; F23R; F23R3/00; F23R3/40
Claims Analysis
Total Claims: 9
Claim 1
Independent Claim
241 words
A method of starting continuous catalytic supported combustion in a gas turbine engine having a main compressor and a turbine in fluid flow communication through a fixed geometry combustion chamber housing the catalytic reactor element therein, said method comprising: rotating the shaft of said main compressor from an external power source to initiate at least some flow from said main compressor to said turbine through said catalytic reactor element; delivering compressed air from a supplemental compressor to a flame holding combustion zone out of the path but in flow communication with the main flow through said combustion chamber upstream of said catalytic reactor element; delivering fuel for mixture with said air in said flame holding zone; igniting said air/fuel mixture in said flame holding zone for self-sustaining continuous combustion therein; passing the hot gases of combustion in said zone into the main path of said combustion chamber for flow through said catalytic reactor element to heat said element; monitoring the temperature of said element and upon said element attaining an auto-combustion temperature therein, initiating main fuel delivery into the main flow of said combustion chamber upstream of said catalytic reactor element for combustion of said main fuel therewithin; and subsequently terminating the delivery of fuel and air to said flame holding combustion zone to extinguish combustion upstream of said cataytic reactor element and regulating the supply of main fuel into said combustion chamber in accordance with the load on said engine.
Claim 2
Independent Claim
241 words
A method of starting continuous catalytic supported combustion in a gas turbine engine having a main compressor and a turbine in fluid flow communication through a fixed geometry combustion chamber housing the catalytic reactor element therein, said method comprising: rotating the shaft of said main compressor from an external power source to initiate at least some flow from said main compressor to said turbine through said catalytic reactor element; delivering compressed air from a supplemental compressor to a flame holding combustion zone out of the path but in flow communication with the main flow through said combustion chamber upstream of said catalytic reactor element; delivering fuel for mixture with said air in said flame holding zone; igniting said air/fuel mixture in said flame holding zone for self-sustaining continuous combustion therein; passing the hot gases of combustion in said zone into the main path of said combustion chamber for flow through said catalytic reactor element to heat said element; monitoring the temperature of said element and upon said element attaining an auto-combustion temperature therein, initiating main fuel delivery into the main flow of said combustion chamber upstream of said catalytic reactor element for combustion of said main fuel therewithin; and subsequently terminating the delivery of fuel and air to said flame holding combustion zone to extinguish combustion upstream of said cataytic reactor element and regulating the supply of main fuel into said combustion chamber in accordance with the load on said engine.
Claim 3
Dependent Claim
27 words
The method of claim 1 wherein said fuel and air delivery to said flame holding zone is terminated upon said catalytic reactor element attaining an auto-combustion temperature.
Claim 4
Dependent Claim
35 words
The method of claim 1 wherein the delivery of said fuel and air to said flame holding combustion zone is terminated in accordance with the shaft of said main compressor attaining a predetermined rotative speed.
Claim 5
Dependent Claim
19 words
The method of claim 3 wherein said predetermined speed is the normal idle speed of said gas turbine engine.
Claim 6
Dependent Claim
222 words
In a gas turbine engine having a compressor and turbine in fluid flow communication through a combustion chamber having a fixed geometry entry for admitting air from the compressor therethrough, and a main fuel nozzle for discharging fuel into said air flow, said chamber having opposed walls for housing a catalytic reactor element therebetween substantially downstream of said entry for effecting combustion of said air and fuel flowing therethrough upon said element having an auto-combustion temperature, and means for heating said element to said temperature comprising: means defining a flame holding combustion zone out of the fluid flow path through said combustion chamber, said means directing the exhaust of said combustion to enter said combustion chamber upstream of said catalytic reactor element; supplemental air compressor means and means for delivering air from said supplemental compressor to said flame holding combustion zone; means for delivering fuel to said flame holding combustion zone for mixture with said supplemental air; means for igniting said air/fuel mixture in said flame holding combustion zone for subsequent continuous combustion therein; whereby the exhaust of said combustion in said flame holding zone enters the combustion chamber for entry into said catalytic reactor element to heat said element to said auto-combustion temperature with said combustion in said zone remaining uneffected by the velocity of fluid passing through said combustion chamber.
Claim 7
Dependent Claim
222 words
In a gas turbine engine having a compressor and turbine in fluid flow communication through a combustion chamber having a fixed geometry entry for admitting air from the compressor therethrough, and a main fuel nozzle for discharging fuel into said air flow, said chamber having opposed walls for housing a catalytic reactor element therebetween substantially downstream of said entry for effecting combustion of said air and fuel flowing therethrough upon said element having an auto-combustion temperature, and means for heating said element to said temperature comprising: means defining a flame holding combustion zone out of the fluid flow path through said combustion chamber, said means directing the exhaust of said combustion to enter said combustion chamber upstream of said catalytic reactor element; supplemental air compressor means and means for delivering air from said supplemental compressor to said flame holding combustion zone; means for delivering fuel to said flame holding combustion zone for mixture with said supplemental air; means for igniting said air/fuel mixture in said flame holding combustion zone for subsequent continuous combustion therein; whereby the exhaust of said combustion in said flame holding zone enters the combustion chamber for entry into said catalytic reactor element to heat said element to said auto-combustion temperature with said combustion in said zone remaining uneffected by the velocity of fluid passing through said combustion chamber.
Claim 8
Dependent Claim
28 words
Structure according to claim 5 wherein said combustion chamber having a fixed geometry entry defines a substantially open inlet end for receiving the discharge from said main compressor.
Claim 9
Dependent Claim
45 words
Structure according to claim 6 wherein said supplemental air delivery means and said fuel delivery means to said flame holding combustion zone include means for terminating the respective flows therethrough, said last named means employed subsequent to said catalytic reactor element attaining an auto-combustion temperature.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1981-09-11 | 1982-03-13 | 1982-09-12 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1985-09-11 | 1986-03-13 | 1986-09-12 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1989-09-11 | 1990-03-13 | 1990-09-12 | $7700.00 | Window Closed / Lapsed |