Patent US4850194A successfully refreshed from Google Patents.
US4850194A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Burner system
Assignee: BBC Brown Boveri AG Switzerland
•
Filing: 1987-12-07
•
Granted: 1989-07-25
•
Expires: 2007-12-07
Abstract
Abstract The present invention relates to a burner system, in particular for a gas turbine, with a main supply channel (2), debouching into a combustion chamber (1), for a fuel/air mixture having a swirler (5) and a burner lance (3) which passes through the swirler (5). To improve the transverse ignition properties between several such burner systems, optionally disposed on the burner chamber (1), and also to increase the flame stability, the burner lance (3) has, on the combustion chamber side with respect to the swirler (5) exit openings (12, 16) for fuel supplied to its interior or for a fuel-rich fuel/air mixture supplied to, or formed in, its interior.
Inventors
- 👤 Cornel Fuglistaller
- 👤 Jakob Keller
- 👤 Thomas Sattelmayer
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-27 19:18
CPC Classifications
F; F23; F23D; F23D14/00; F23D14/26; F23D11/00; F23D14/02; Y; Y02; Y02E; Y02E20/00; Y02E20/34
Claims Analysis
Total Claims: 7
Claim 1
Independent Claim
170 words
A burner system for a gas turbine, comprising: a combustion chamber; a main supply channel debouching into the combustion chamber; a swirler arranged in the main supply channel; a burner lance extending through the swirler; a fuel channel provided in the interior of the burner lance, said fuel channel having first exit openings leading radially outwardly into the combustion chamber; a premix chamber provided in the interior of the burner lance; a combustion air channel provided in the interior of the burner lance; said fuel channel and said combustion air channel debouching into the premix chamber via debouchement openings; second exit openings from the premix chamber leading axially outwardly into the combustion chamber; said premix chamber being an annular chamber, wherein the second exit openings are distributed about the circumference of the premix chamber; and said first exit openings being dimensioned in relation to the debouchement openings extending into the premix chamber such that a majority of the fuel supplied to the combustion chamber emerges through the first exit openings.
Claim 2
Dependent Claim
170 words
A burner system for a gas turbine, comprising: a combustion chamber; a main supply channel debouching into the combustion chamber; a swirler arranged in the main supply channel; a burner lance extending through the swirler; a fuel channel provided in the interior of the burner lance, said fuel channel having first exit openings leading radially outwardly into the combustion chamber; a premix chamber provided in the interior of the burner lance; a combustion air channel provided in the interior of the burner lance; said fuel channel and said combustion air channel debouching into the premix chamber via debouchement openings; second exit openings from the premix chamber leading axially outwardly into the combustion chamber; said premix chamber being an annular chamber, wherein the second exit openings are distributed about the circumference of the premix chamber; and said first exit openings being dimensioned in relation to the debouchement openings extending into the premix chamber such that a majority of the fuel supplied to the combustion chamber emerges through the first exit openings.
Claim 3
Dependent Claim
41 words
The burner system as claimed in claim 1, wherein the first exit openings are so dimensioned in relation to the debouchement openings into the premix chamber that between 85% and 95% of the fuel supplied emerges through the first exit openings.
Claim 4
Dependent Claim
46 words
The burner system as claimed in claim 1, wherein the debouchement openings of the fuel channel and the combustion air channel into the premix chamber are so dimensioned that a fuel/air mixture with an air/fuel ratio between 0.3 and 1.0 is established in the premix chamber.
Claim 5
Dependent Claim
49 words
The burner arrangement as claimed in claim 1, wherein the second exit openings of the premix chamber are so dimensioned that the velocity of the mixture flow emerging from them is greater than 25% of the velocity of the flow entering the combustion chamber from the main supply channel.
Claim 6
Dependent Claim
52 words
The burner system as claimed in claim 1, further comprising a cylindrical guide plate which simultaneously forms the inner termination of the swirler, wherein a gap is formed between the burner lance and the guide plate, and wherein the cross-section of the burner lance is reduced in the region of the gap.
Claim 7
Dependent Claim
35 words
The burner system as claimed in claim 1, wherein a supply of fuel or of a fuel/air mixture via the exit openings of the burner lance is regulable, and in particular can be shut off.
References Cited (Backward Citations)
GB1031184A
Cited
US3630024A
Cited
US3764071A
Cited
US3788067A
Cited
US3777983A
Cited
US3937011A
Cited
US3866413A
Cited
US4260367A
Cited
US4373325A
Cited
EP0095788A1
Cited
EP0108361A1
Cited
DE3606625A1
Cited
EP0193838B1
Cited
US4726192A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1992-07-24 | 1993-01-23 | 1993-07-25 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1996-07-24 | 1997-01-23 | 1997-07-25 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2000-07-24 | 2001-01-23 | 2001-07-25 | $7700.00 | Window Closed / Lapsed |