US3886728A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Combustor prechamber
Assignee: Motors Liquidation Co
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Filing: 1974-05-01
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Granted: 1975-06-03
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Expires: 1994-05-01
Abstract
Abstract A combustion liner for a gas turbine combustion apparatus has a prechamber for mixing of fuel and combustion air. Air enters the prechamber with a radially outward and tangential flow through a cylindrical swirler. The swirler is movable axially to reduce its axial length and thus the effective area of the swirler to control the primary air flow into the prechamber and on into the reaction zone of the combustion liner. Fuel is scoured off the outer wall of the prechamber and preferably vaporized by the air flowing with swirling movement from the air inlet to the reaction zone.
Inventors
- 👤 Ronald E Quinn
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-26 01:28
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/28; F23R3/30; F23R3/02; F23R3/04; F23R3/10; F23R3/12; F23R3/14; F23R3/26; F05; F05B; F05B2250/00; F05B2250/40; F05B2250/41
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
160 words
A combustion liner for a gas turbine combustion apparatus or the like comprising a wall extending from an upstream end to a downstream end of the liner defining, in flow sequence, a prechamber, a reaction zone, a dilution zone, and an outlet for combustion products, the prechamber wall having a substantially circular cross section; means for delivering fuel to the inner surface of the prechamber wall; means defining an annular radial outflow air inlet at the upstream end of the prechamber, the air inlet extending circumferentially and axially of the prechamber upstream of the fuel delivering means; an air swirling and throttling cylinder disposed across the said air inlet movable axially of the prechamber, the cylinder bearing a set of swirl vanes adapted to direct the air outwardly and circumferentially from the inlet into the prechamber, the area of the set of swirl vanes being variable by axial movement of the cylinder to vary primary air flow into the liner.
Claim 2
Dependent Claim
160 words
A combustion liner for a gas turbine combustion apparatus or the like comprising a wall extending from an upstream end to a downstream end of the liner defining, in flow sequence, a prechamber, a reaction zone, a dilution zone, and an outlet for combustion products, the prechamber wall having a substantially circular cross section; means for delivering fuel to the inner surface of the prechamber wall; means defining an annular radial outflow air inlet at the upstream end of the prechamber, the air inlet extending circumferentially and axially of the prechamber upstream of the fuel delivering means; an air swirling and throttling cylinder disposed across the said air inlet movable axially of the prechamber, the cylinder bearing a set of swirl vanes adapted to direct the air outwardly and circumferentially from the inlet into the prechamber, the area of the set of swirl vanes being variable by axial movement of the cylinder to vary primary air flow into the liner.
Claim 3
Dependent Claim
160 words
A combustion liner for a gas turbine combustion apparatus or the like comprising a wall extending from an upstream end to a downstream end of the liner defining, in flow sequence, a prechamber, a reaction zone, a dilution zone, and an outlet for combustion products, the prechamber wall having a substantially circular cross section; means for delivering fuel to the inner surface of the prechamber wall; means defining an annular radial outflow air inlet at the upstream end of the prechamber, the air inlet extending circumferentially and axially of the prechamber upstream of the fuel delivering means; an air swirling and throttling cylinder disposed across the said air inlet movable axially of the prechamber, the cylinder bearing a set of swirl vanes adapted to direct the air outwardly and circumferentially from the inlet into the prechamber, the area of the set of swirl vanes being variable by axial movement of the cylinder to vary primary air flow into the liner.
Claim 4
Dependent Claim
160 words
A combustion liner for a gas turbine combustion apparatus or the like comprising a wall extending from an upstream end to a downstream end of the liner defining, in flow sequence, a prechamber, a reaction zone, a dilution zone, and an outlet for combustion products, the prechamber wall having a substantially circular cross section; means for delivering fuel to the inner surface of the prechamber wall; means defining an annular radial outflow air inlet at the upstream end of the prechamber, the air inlet extending circumferentially and axially of the prechamber upstream of the fuel delivering means; an air swirling and throttling cylinder disposed across the said air inlet movable axially of the prechamber, the cylinder bearing a set of swirl vanes adapted to direct the air outwardly and circumferentially from the inlet into the prechamber, the area of the set of swirl vanes being variable by axial movement of the cylinder to vary primary air flow into the liner.
Claim 5
Dependent Claim
181 words
A combustion liner for a gas turbine combustion apparatus or the like comprising a wall extending from an upstream end to a downstream end of the liner defining, in flow sequence, a prechamber, a reaction zone, a dilution zone, and an outlet for combustion products, the prechamber wall having a substantially circular cross section; means for delivering fuel to the inner surface of the prechamber wall; means defining an annular radial outflow air inlet at the upstream end of the prechamber; a centerbody defining with the prechamber wall an annular flow path leading from the inlet to the reaction zone; the air inlet extending circumferentially and axially of the prechamber upstream of the fuel delivering means and centerbody; an air swirling and throttling cylinder disposed across the said air inlet movable axially of the prechamber, the cylinder bearing a set of swirl vanes adapted to direct the air outwardly and circumferentially from the inlet into the prechamber, the area of the set of swirl vanes being variable by axial movement of the cylinder to vary primary air flow into the liner.
Claim 6
Dependent Claim
181 words
A combustion liner for a gas turbine combustion apparatus or the like comprising a wall extending from an upstream end to a downstream end of the liner defining, in flow sequence, a prechamber, a reaction zone, a dilution zone, and an outlet for combustion products, the prechamber wall having a substantially circular cross section; means for delivering fuel to the inner surface of the prechamber wall; means defining an annular radial outflow air inlet at the upstream end of the prechamber; a centerbody defining with the prechamber wall an annular flow path leading from the inlet to the reaction zone; the air inlet extending circumferentially and axially of the prechamber upstream of the fuel delivering means and centerbody; an air swirling and throttling cylinder disposed across the said air inlet movable axially of the prechamber, the cylinder bearing a set of swirl vanes adapted to direct the air outwardly and circumferentially from the inlet into the prechamber, the area of the set of swirl vanes being variable by axial movement of the cylinder to vary primary air flow into the liner.
Claim 7
Dependent Claim
179 words
A combustion liner for a gas turbine combustion apparatus or the like comprising a wall extending from an upstream end to a downstream end of the liner defining, in flow sequence, a prechamber, a reaction zone, a dilution zone, and an outlet for combustion products, the prechamber wall having a substantially circular cross section; means for delivering fuel to the inner surface of the prechamber wall; means defining an annular radial outflow air inlet at the upstream end of the prechamber; the prechamber wall being divergent at the air inlet and convergent through the downstream portion of the flow path; the air inlet extending circumferentially and axially of the prechamber upstream of the fuel delivering means; an air swirling and throttling cylinder disposed across the said air inlet movable axially of the prechamber, the cylinder bearing a set of swirl vanes adapted to direct the air outwardly and circumferentially from the inlet into the prechamber, the area of the set of swirl vanes being variable by axial movement of the cylinder to vary primary air flow into the liner.
Claim 8
Dependent Claim
179 words
A combustion liner for a gas turbine combustion apparatus or the like comprising a wall extending from an upstream end to a downstream end of the liner defining, in flow sequence, a prechamber, a reaction zone, a dilution zone, and an outlet for combustion products, the prechamber wall having a substantially circular cross section; means for delivering fuel to the inner surface of the prechamber wall; means defining an annular radial outflow air inlet at the upstream end of the prechamber; the prechamber wall being divergent at the air inlet and convergent through the downstream portion of the flow path; the air inlet extending circumferentially and axially of the prechamber upstream of the fuel delivering means; an air swirling and throttling cylinder disposed across the said air inlet movable axially of the prechamber, the cylinder bearing a set of swirl vanes adapted to direct the air outwardly and circumferentially from the inlet into the prechamber, the area of the set of swirl vanes being variable by axial movement of the cylinder to vary primary air flow into the liner.
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) | 1978-06-02 | 1978-12-02 | 1979-06-03 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-06-02 | 1982-12-02 | 1983-06-03 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-06-02 | 1986-12-02 | 1987-06-03 | $7700.00 | Window Closed / Lapsed |