US3893296A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Combustion liner
Assignee: Motors Liquidation Co
•
Filing: 1974-07-01
•
Granted: 1975-07-08
•
Expires: 1994-07-01
Abstract
Abstract A combustion liner, for a gas turbine or similar use, provides for introduction of fuel and primary air and premixing of the fuel with the air before entry into the reaction zone of the combustion liner. Air is swirled radially inwardly past a fuel spray ring at the upstream end of the liner and then into a premix chamber of greater diameter than the swirler. The premix chamber has a downstream wall at the center of which is a throat through which the fuel-air mixture enters a divergent reaction zone. An axially movable support which enters through the upstream end bears two disks. One disk throttles flow of air through the swirler and the other varies the area of the annular outlet from the premix chamber between the disk and the downstream wall.
Inventors
- 👤 Hans P Fredriksen
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-26 11:03
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/28; F23R3/30
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
166 words
A combustion liner adapted for high energy combustion and with provisions for maintaining a desired equivalence ratio in the reaction zone, the liner having a closed upstream end and having a substantially circular cross-section, and comprising a radial-inflow primary air inlet swirler closely adjacent to the upstream end with flow through circumferentially distributed slots extending axially of the liner; a premixing chamber juxtaposed to and coaxial with the swirler and having a diameter greater than that of the swirler, the premixing chamber having a generally radial annular downstream wall converging to a throat; means defining a reaction zone connected to the premixing chamber through the throat; a first flow controlling disk reciprocable axially of the liner to close variably the air swirler slots to vary primary air flow; fuel spray means disposed at the upstream end of the premixing chamber; and a second flow controlling disk reciprocable toward and from the said downstream wall to vary flow area from the premixing chamber into the said throat.
Claim 2
Dependent Claim
166 words
A combustion liner adapted for high energy combustion and with provisions for maintaining a desired equivalence ratio in the reaction zone, the liner having a closed upstream end and having a substantially circular cross-section, and comprising a radial-inflow primary air inlet swirler closely adjacent to the upstream end with flow through circumferentially distributed slots extending axially of the liner; a premixing chamber juxtaposed to and coaxial with the swirler and having a diameter greater than that of the swirler, the premixing chamber having a generally radial annular downstream wall converging to a throat; means defining a reaction zone connected to the premixing chamber through the throat; a first flow controlling disk reciprocable axially of the liner to close variably the air swirler slots to vary primary air flow; fuel spray means disposed at the upstream end of the premixing chamber; and a second flow controlling disk reciprocable toward and from the said downstream wall to vary flow area from the premixing chamber into the said throat.
Claim 3
Dependent Claim
170 words
A combustion liner adapted for high energy combustion and with provisions for maintaining a desired equivalence ratio in the reaction zone, the liner having a closed upstream end and having a substantially circular cross-section, and comprising a radial-inflow primary air inlet swirler closely adjacent to the upstream end with flow through circumferentially distributed slots extending axially of the liner; a premixing chamber juxtaposed to and coaxial with the swirler and having a diameter greater than that of the swirler, the premixing chamber having a generally radial annular downstream wall converging to a throat; means defining a reaction zone connected to the premixing chamber through the throat; a first flow controlling disk reciprocable to close variably the air swirler slots to vary primary air flow; a fuel spray ring disposed at the upstream end of the premixing chamber; and a second flow controlling disk reciprocable concurrently with the first flow controlling disk toward and from the said downstream wall to vary flow area from the premixing chamber to the said throat.
Claim 4
Dependent Claim
170 words
A combustion liner adapted for high energy combustion and with provisions for maintaining a desired equivalence ratio in the reaction zone, the liner having a closed upstream end and having a substantially circular cross-section, and comprising a radial-inflow primary air inlet swirler closely adjacent to the upstream end with flow through circumferentially distributed slots extending axially of the liner; a premixing chamber juxtaposed to and coaxial with the swirler and having a diameter greater than that of the swirler, the premixing chamber having a generally radial annular downstream wall converging to a throat; means defining a reaction zone connected to the premixing chamber through the throat; a first flow controlling disk reciprocable to close variably the air swirler slots to vary primary air flow; a fuel spray ring disposed at the upstream end of the premixing chamber; and a second flow controlling disk reciprocable concurrently with the first flow controlling disk toward and from the said downstream wall to vary flow area from the premixing chamber to the said throat.
Claim 5
Dependent Claim
178 words
A combustion liner adapted for high energy combustion and with provisions for maintaining a desired equivalence ratio in the reaction zone, the liner having a closed upstream end and having a substantially circular cross-section, and comprising a radial-inflow primary air inlet swirler closely adjacent to the upstream end with flow through circumferentially distributed slots extending axially of the liner; a premixing chamber juxtaposed to and coaxial with the swirler and having a diameter greater than that of the swirler, the premixing chamber having a generally radial annular downstream wall converging to a throat; means defining a reaction zone connected to the premixing chamber through the throat; a support movable axially of the liner; a first flow controlling disk mounted on the support reciprocable to close variably the air swirler slots to vary primary air flow; fuel spray means disposed at the upstream end of the premixing chamber; and a second flow controlling disk mounted on the support for reciprocation toward and from the said downstream wall to vary flow area from the premixing chamber to the said throat.
Claim 6
Dependent Claim
178 words
A combustion liner adapted for high energy combustion and with provisions for maintaining a desired equivalence ratio in the reaction zone, the liner having a closed upstream end and having a substantially circular cross-section, and comprising a radial-inflow primary air inlet swirler closely adjacent to the upstream end with flow through circumferentially distributed slots extending axially of the liner; a premixing chamber juxtaposed to and coaxial with the swirler and having a diameter greater than that of the swirler, the premixing chamber having a generally radial annular downstream wall converging to a throat; means defining a reaction zone connected to the premixing chamber through the throat; a support movable axially of the liner; a first flow controlling disk mounted on the support reciprocable to close variably the air swirler slots to vary primary air flow; fuel spray means disposed at the upstream end of the premixing chamber; and a second flow controlling disk mounted on the support for reciprocation toward and from the said downstream wall to vary flow area from the premixing chamber to the said throat.
Claim 7
Dependent Claim
202 words
A combustion liner adapted for high energy combustion and with provisions for maintaining a desired equivalence ratio in the reaction zone, the liner having a closed upstream end and having a substantially circular cross-section, and comprising a radiaL-inflow primary air inlet swirler closely adjacent to the upstream end with flow through circumferentially distributed slots extending axially of the liner; a premixing chamber juxtaposed to and coaxial with the swirler and having a diameter greater than that of the swirler, the premixing chamber having a generally radial annular downstream wall converging to a throat; wall means defining a diverging reaction zone connected to the premixing chamber through the throat; a support movable axially of the liner extending through the upstream end of the liner; a first flow controlling disk mounted on the support reciprocable to close variably the air swirler slots to vary primary air flow; a fuel spray ring disposed at the upstream end of the premixing chamber; a second flow controlling disk mounted on the support for reciprocation toward and from the said downstream wall to vary flow area from the premixing chamber into the said throat; and an igniter mounted downstream of the second flow controlling disk on the support.
Claim 8
Dependent Claim
202 words
A combustion liner adapted for high energy combustion and with provisions for maintaining a desired equivalence ratio in the reaction zone, the liner having a closed upstream end and having a substantially circular cross-section, and comprising a radiaL-inflow primary air inlet swirler closely adjacent to the upstream end with flow through circumferentially distributed slots extending axially of the liner; a premixing chamber juxtaposed to and coaxial with the swirler and having a diameter greater than that of the swirler, the premixing chamber having a generally radial annular downstream wall converging to a throat; wall means defining a diverging reaction zone connected to the premixing chamber through the throat; a support movable axially of the liner extending through the upstream end of the liner; a first flow controlling disk mounted on the support reciprocable to close variably the air swirler slots to vary primary air flow; a fuel spray ring disposed at the upstream end of the premixing chamber; a second flow controlling disk mounted on the support for reciprocation toward and from the said downstream wall to vary flow area from the premixing chamber into the said throat; and an igniter mounted downstream of the second flow controlling disk on the support.
References Cited (Backward Citations)
US1490008A
Cited
US2595759A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1978-07-07 | 1979-01-06 | 1979-07-08 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-07-07 | 1983-01-06 | 1983-07-08 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-07-07 | 1987-01-06 | 1987-07-08 | $7700.00 | Window Closed / Lapsed |