US3826080A
Expired / Lapsed
US
⏱️ 0.0 years remaining
System for reducing nitrogen-oxygen compound in the exhaust of a gas turbine
Assignee: Westinghouse Electric Corp
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Filing: 1973-03-15
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Granted: 1974-07-30
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Expires: 1993-03-15
Abstract
Abstract To reduce nitrogen-oxygen compounds in the exhaust of a gas turbine water is supplied to a fuel injection nozzle via the atomizing air passages disposed therein providing a coolant fluid directly to the primary combustion zone.
Inventors
- 👤 Corso S De
- 👤 C Hussey
- 👤 M Ambrose
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-26 17:13
CPC Classifications
F; F02; F02C; F02C3/00; F02C3/20; F02C3/30
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
101 words
A gas turbine comprising a combustion chamber, a fuel injection nozzle for supplying fuel to the combustion chamber, said fuel injection nozzle having an atomizing air passageway and a plurality of orifices which are utilized during ignition and low fuel flows to atomize the influent fuel entering the combustion chamber, means for shutting off the atomizing air to said passageway and orifices and means for supplying a pressurized coolant fluid to said passageway and orifices whereby the coolant fluid admixes with the burning fuel and thereby reduces the flame termperature and the quantity of nitrogenoxygen compounds produced in the combustion chamber.
Claim 2
Dependent Claim
101 words
A gas turbine comprising a combustion chamber, a fuel injection nozzle for supplying fuel to the combustion chamber, said fuel injection nozzle having an atomizing air passageway and a plurality of orifices which are utilized during ignition and low fuel flows to atomize the influent fuel entering the combustion chamber, means for shutting off the atomizing air to said passageway and orifices and means for supplying a pressurized coolant fluid to said passageway and orifices whereby the coolant fluid admixes with the burning fuel and thereby reduces the flame termperature and the quantity of nitrogenoxygen compounds produced in the combustion chamber.
Claim 3
Dependent Claim
15 words
A gas turbine as set forth in claim 1, wherein the coolant fluid is water.
Claim 4
Dependent Claim
51 words
A gas turbine as set forth in claim 1, wherein the air atomizing orifices are so disposed that the coolant fluid leaving the fuel injection nozzle forms a plurality of discrete jets skewed with respect to the axis of the injection nozzle and inclined at a compound angle with respect thereto.
Claim 5
Dependent Claim
48 words
A gas turbine as set forth in claim 1, wherein the fuel injection nozzle has a fuel passageway and orifice so arranged that the fuel leaving the fuel injection nozzle generally forms a diverging hollow conical shape spray with the apex adjacent the end of the injection nozzle.
Claim 6
Dependent Claim
56 words
A gas turbine as set forth in claim 4, wherein the fuel injection nozzle has the atomizing air passageway and orifices so arranged that the coolant fluid leaving the nozzle forms a plurality of discrete jets skewed with respect to the axis of the injection nozzle and inclined generally at a compound angle with respect thereto.
Claim 7
Dependent Claim
15 words
A gas turbine as set forth in claim 4, wherein this coolant fluid is water.
Claim 8
Dependent Claim
141 words
A gas turbine comprising a combustion chamber, a fuel injection nozzle for supplying fuel to the combustion chamber and disposed adjacent one end thereof, said fuel injection nozzle being supplied with a liquid fuel and a coolant fluid and having a fuel passageway and orifice so disposed therein that the fuel leaving the injection nozzle generally forms a diverging conical shaped hollow spray and the fuel injection nozzle having a coolant fluid passageway and a plurality of orifices so arranged that the coolant fluid leaving the injection nozzle forms a plurality of discrete jets skewed with respect to the axis of the injection nozzle and inclined generally at a compound angle with respect thereto, whereby said fluid coolant admixes with said fuel as it burns to reduce the flame temperature and the formation of nitrogen-oxygen compounds formed in the combustion chamber.
Claim 9
Dependent Claim
141 words
A gas turbine comprising a combustion chamber, a fuel injection nozzle for supplying fuel to the combustion chamber and disposed adjacent one end thereof, said fuel injection nozzle being supplied with a liquid fuel and a coolant fluid and having a fuel passageway and orifice so disposed therein that the fuel leaving the injection nozzle generally forms a diverging conical shaped hollow spray and the fuel injection nozzle having a coolant fluid passageway and a plurality of orifices so arranged that the coolant fluid leaving the injection nozzle forms a plurality of discrete jets skewed with respect to the axis of the injection nozzle and inclined generally at a compound angle with respect thereto, whereby said fluid coolant admixes with said fuel as it burns to reduce the flame temperature and the formation of nitrogen-oxygen compounds formed in the combustion chamber.
Claim 10
Dependent Claim
15 words
A gas turbine as set forth in claim 7, wherein the coolant fluid is water.
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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) | 1977-07-29 | 1978-01-28 | 1978-07-30 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1981-07-29 | 1982-01-28 | 1982-07-30 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1985-07-29 | 1986-01-28 | 1986-07-30 | $7700.00 | Window Closed / Lapsed |