US5901549A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Pilot burner fuel nozzle with uneven fuel injection for premixed type combustor producing long and short flames
Assignee: Mitsubishi Power Ltd
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Filing: 1997-04-30
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Granted: 1999-05-11
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Expires: 2017-04-30
Abstract
Abstract In a pilot burner fuel nozzle for a premixed type combustor, diffusion pilot fuel injection ports (fuel holes 101) are disposed unevenly in the circumferential direction, whereby a nonuniform pilot flame is formed in the circumferential direction in the premixed type combustor. Thereupon, the heat is distributed in the axial direction, so that oscillated combustion does not occur, by which stable combustion can be maintained.
Inventors
- 👤 Shigemi Mandai
- 👤 Hiroyuki Nishida
- 👤 Satoshi Tanimura
- 👤 Jun Kubota
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-28 07:15
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/28; F23R3/34; F23R3/343; F02; F02C; F02C7/00; F02C7/22; F02C7/228; F02C9/00; F02C9/26; F23D; F23D23/00; F23M; F23M20/00; F23M20/005; F23D2210/00; F23R2900/00; F23R2900/00014
Claims Analysis
Total Claims: 14
Claim 1
Independent Claim
154 words
A premixed type combustor, comprising: a combustor chamber; an elongate pilot fuel nozzle within said combustor chamber; and a plurality of main fuel nozzles arranged peripherally with respect to said pilot fuel nozzle and operative to form a premixed gas within said combustor chamber, said elongate pilot fuel nozzle having a plurality of fuel injection ports unevenly spaced circumferentially around the elongate axis of said pilot fuel nozzle so that said pilot fuel nozzle is operative to provide a pilot flame that is unevenly circumferentially arranged around said elongate axis so that said pilot flame causes a first portion of said premixed gas in a first region of said combustor chamber to burn with a short flame and a second portion of said premixed gas in a second region of said combustor chamber to burn with a long flame, whereby heat is distributed in the direction of said elongate axis to diminish oscillated combustion.
Claim 2
Dependent Claim
154 words
A premixed type combustor, comprising: a combustor chamber; an elongate pilot fuel nozzle within said combustor chamber; and a plurality of main fuel nozzles arranged peripherally with respect to said pilot fuel nozzle and operative to form a premixed gas within said combustor chamber, said elongate pilot fuel nozzle having a plurality of fuel injection ports unevenly spaced circumferentially around the elongate axis of said pilot fuel nozzle so that said pilot fuel nozzle is operative to provide a pilot flame that is unevenly circumferentially arranged around said elongate axis so that said pilot flame causes a first portion of said premixed gas in a first region of said combustor chamber to burn with a short flame and a second portion of said premixed gas in a second region of said combustor chamber to burn with a long flame, whereby heat is distributed in the direction of said elongate axis to diminish oscillated combustion.
Claim 3
Dependent Claim
54 words
The premixed type combustor of claim 1, wherein said uneven circumferential spacing of said fuel injection ports around said elongate axis is operative so that said pilot flame is present in said first region and absent in said second region, so that said long flame is established by flame propagation from said short flame.
Claim 4
Dependent Claim
43 words
The premixed type combustor of claim 1, further comprising a cone within said combustor chamber, wherein said pilot fuel nozzle is positioned within said cone and said main fuel nozzles are external of said cone and arranged peripherally with respect to said cone.
Claim 5
Dependent Claim
67 words
The premixed type combustor of claim 1, wherein: said pilot fuel nozzle comprises a downstream end within said combustor chamber; said fuel injection ports are positioned upstream of said downstream end; and said pilot fuel nozzle further comprises a downstream group of fuel injection ports that are proximate to said downstream end and displaced along said elongate axis from said upstream group of pilot fuel injection ports.
Claim 6
Dependent Claim
23 words
The premixed type combustor of claim 4, wherein said downstream group of fuel injection ports is evenly angularly arranged around said elongate axis.
Claim 7
Dependent Claim
200 words
A premixed type combustor, comprising: a combustor chamber; an elongate pilot fuel nozzle within said combustor chamber; and a plurality of main fuel nozzles arranged peripherally with respect to said pilot fuel nozzle and operative to form a premixed gas within said combustor chamber, said elongate pilot fuel nozzle having a plurality of fuel injection ports defining an uneven circumferential spacing around the elongate axis of said pilot fuel nozzle so that said pilot fuel nozzle is operative to provide a pilot flame that is unevenly circumferentially arranged around said elongate axis so that said pilot flame causes a first portion of said premixed gas in a first region of said combustor chamber to burn with a short flame and a second portion of said premixed gas in a second region of said combustor chamber to burn with a long flame, whereby heat is distributed in the direction of said elongate axis to diminish oscillated combustion, and wherein said plurality of fuel injection ports comprises an upstream group of fuel injection ports and a group of downstream fuel injection ports that are downstream from said upstream fuel injection ports, and said upstream fuel injection ports define said uneven circumferential spacing.
Claim 8
Dependent Claim
200 words
A premixed type combustor, comprising: a combustor chamber; an elongate pilot fuel nozzle within said combustor chamber; and a plurality of main fuel nozzles arranged peripherally with respect to said pilot fuel nozzle and operative to form a premixed gas within said combustor chamber, said elongate pilot fuel nozzle having a plurality of fuel injection ports defining an uneven circumferential spacing around the elongate axis of said pilot fuel nozzle so that said pilot fuel nozzle is operative to provide a pilot flame that is unevenly circumferentially arranged around said elongate axis so that said pilot flame causes a first portion of said premixed gas in a first region of said combustor chamber to burn with a short flame and a second portion of said premixed gas in a second region of said combustor chamber to burn with a long flame, whereby heat is distributed in the direction of said elongate axis to diminish oscillated combustion, and wherein said plurality of fuel injection ports comprises an upstream group of fuel injection ports and a group of downstream fuel injection ports that are downstream from said upstream fuel injection ports, and said upstream fuel injection ports define said uneven circumferential spacing.
Claim 9
Dependent Claim
46 words
The premixed type combustor of claim 6, wherein said uneven circumferential spacing is operative to provide that said pilot flame is present in said first region and absent in said second region, so that said long flame is established by flame propagation from said short flame.
Claim 10
Dependent Claim
42 words
The premixed type combustor of claim 6, further comprising a cone within said combustor chamber, wherein said pilot fuel nozzle is within said cone and said main fuel nozzles are external of said cone and arranged peripherally with respect to said cone.
Claim 11
Dependent Claim
21 words
The premixed type combustor of claim 6, wherein said downstream fuel injection ports are evenly circumferentially spaced around said elongate axis.
Claim 12
Independent Claim
122 words
A method of combusting in a premixed type combustor chamber, comprising the steps of: forming a premixed gas within the combustor chamber; and providing a pilot flame from an elongate pilot fuel nozzle within the combustor chamber so that the pilot flame is unevenly circumferentially arranged around the elongate axis of the pilot fuel nozzle and so that the pilot flame causes a first portion of the premixed gas in a first region of the combustor chamber to burn with a short flame and a second portion of the premixed gas in a second region of the combustor chamber to burn with a long flame, so that heat is distributed in the direction of the elongate axis and oscillated combustion is diminished.
Claim 13
Independent Claim
122 words
A method of combusting in a premixed type combustor chamber, comprising the steps of: forming a premixed gas within the combustor chamber; and providing a pilot flame from an elongate pilot fuel nozzle within the combustor chamber so that the pilot flame is unevenly circumferentially arranged around the elongate axis of the pilot fuel nozzle and so that the pilot flame causes a first portion of the premixed gas in a first region of the combustor chamber to burn with a short flame and a second portion of the premixed gas in a second region of the combustor chamber to burn with a long flame, so that heat is distributed in the direction of the elongate axis and oscillated combustion is diminished.
Claim 14
Dependent Claim
37 words
The method of claim 10, wherein the pilot flame is present in the first region and is not present in the second region, so that the long flame is established by flame propagation from the short flame.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 2002-05-10 | 2002-11-09 | 2003-05-11 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2006-05-10 | 2006-11-09 | 2007-05-11 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2010-05-10 | 2010-11-09 | 2011-05-11 | $7700.00 | Window Closed / Lapsed |