US3859787A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Combustion apparatus
Assignee: Motors Liquidation Co
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Filing: 1974-02-04
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Granted: 1975-01-14
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Expires: 1994-02-04
Abstract
Abstract A combustion apparatus for gas turbine engines particularly adapted to reduce emissions to meet automotive requirements. The fuel is laid on the wall of a cylindrical prechamber and evaporated from the wall by combustion air which is introduced through a swirler at the upstream end of the prechamber. The inner surface of the prechamber is artificially roughened by a grid of grooves to improve fuel evaporation. The fuel is laid on the wall from an annular manifold extending around the upstream end of the prechamber through tangential orifices leading from the manifold into the interior of the prechamber. The fuel manifold is cooled and shielded from heat by an air jacket. More air enters through entrance ports distributed around the prechamber toward its downstream end. The resulting lean fuel-air mixture is delivered past an annular flow dam at the outlet of the prechamber into a combustion or reaction zone which is abruptly enlarged from the prechamber. The structure causes turbulent flow, recirculation, and good mixing in the reaction zone. A dilution zone downstream at the reaction zone has a circumferential array of dilution air ports which are of such shape as to be varied nonlinearly in area by a sliding ring valve. The sliding ring valve is coupled to a second sliding ring valve which varies the area of the air entrance ports in the prechamber in reverse sense to the dilution air ports. A pilot fuel nozzle to aid in cold starts is mounted at the upstream end of the prechamber.
Inventors
- 👤 Robert D Anderson
- 👤 Dennis L Troth
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 15:28
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/02; F23R3/26; F02; F02C; F02C7/00; F02C7/12; F02C7/14; F23R3/28; F23R3/30; F05; F05D; F05D2250/00; F05D2250/40; F05D2250/41; F05D2250/411
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
219 words
A combustion apparatus adapted for use in a gas turbine engine characterized by substantially complete combustion of liquid hydrocarbon fuel and by a low output of nitrogen oxides, the apparatus comprising a combustion liner having a discharge outlet for combustion products at the downstream end of the liner; the liner having an upstream end and liner wall means extending from the upstream end to the downstream end, the wall means enclosing, in sequence from the upstream end to the downstream end, a prechamber, a reaction zone, and a dilution zone; the prechamber including air entrance means at its upstream end effective to direct combustion air with substantial velocity downstream over the inner surface of the prechamber wall means, and liquid fuel introduction means downstream of the said air entrance means disposed to lay a film of liquid fuel on the said inner surface for evaporation by and mixture in the prechamber with the said combustion air, wherein the improvement comprises a textured configuration of the said prechamber wall means inner surface defined by a grid of two sets of intersecting grooves in the surface and bosses rising between adjacent grooves, adapted to allow flow of the liquid fuel through the grooves and evaporation of the fuel from within the grooves by the flow of air over the said surface.
Claim 2
Dependent Claim
219 words
A combustion apparatus adapted for use in a gas turbine engine characterized by substantially complete combustion of liquid hydrocarbon fuel and by a low output of nitrogen oxides, the apparatus comprising a combustion liner having a discharge outlet for combustion products at the downstream end of the liner; the liner having an upstream end and liner wall means extending from the upstream end to the downstream end, the wall means enclosing, in sequence from the upstream end to the downstream end, a prechamber, a reaction zone, and a dilution zone; the prechamber including air entrance means at its upstream end effective to direct combustion air with substantial velocity downstream over the inner surface of the prechamber wall means, and liquid fuel introduction means downstream of the said air entrance means disposed to lay a film of liquid fuel on the said inner surface for evaporation by and mixture in the prechamber with the said combustion air, wherein the improvement comprises a textured configuration of the said prechamber wall means inner surface defined by a grid of two sets of intersecting grooves in the surface and bosses rising between adjacent grooves, adapted to allow flow of the liquid fuel through the grooves and evaporation of the fuel from within the grooves by the flow of air over the said surface.
Claim 3
Dependent Claim
244 words
A combustion apparatus adapted for use in a gas turbine engine characterized by substantially complete combustion of liquid hydrocarbon fuel and by a low output of nitrogen oxides, the apparatus comprising a combustion liner having a discharge outlet for combustion products at the downstream end of the liner; the liner having an upstream end and liner wall means extending from the upstream end to the downstream end, the wall means enclosing, in sequence from the stream end to the downstream end, a prechamber, a reaction zone, and a dilution zone; the prechamber including air entrance means defined by swirler means at its upstream end effective to direct combustion air with a substantial transverse velocity component downstream over the inner surface of the prechamber wall means, and liquid fuel introduction means downstream of the said air entrance means disposed to lay a film of liquid fuel on the said inner surface for evaporation by and mixture in the prechamber with the said combustion air, wherein the improvement comprises a textured configuration of the said prechamber wall means inner surface defined by a grid of two sets of intersecting grooves in the surface and generally rectangular bosses rising between adjacent grooves, adapted to allow flow of the liquid fuel through the grooves and evaporation of the fuel from within the grooves by the flow of air over the said surface, the grooves being disposed at roughly a 45* angle to the axial direction through the prechamber.
Claim 4
Dependent Claim
244 words
A combustion apparatus adapted for use in a gas turbine engine characterized by substantially complete combustion of liquid hydrocarbon fuel and by a low output of nitrogen oxides, the apparatus comprising a combustion liner having a discharge outlet for combustion products at the downstream end of the liner; the liner having an upstream end and liner wall means extending from the upstream end to the downstream end, the wall means enclosing, in sequence from the stream end to the downstream end, a prechamber, a reaction zone, and a dilution zone; the prechamber including air entrance means defined by swirler means at its upstream end effective to direct combustion air with a substantial transverse velocity component downstream over the inner surface of the prechamber wall means, and liquid fuel introduction means downstream of the said air entrance means disposed to lay a film of liquid fuel on the said inner surface for evaporation by and mixture in the prechamber with the said combustion air, wherein the improvement comprises a textured configuration of the said prechamber wall means inner surface defined by a grid of two sets of intersecting grooves in the surface and generally rectangular bosses rising between adjacent grooves, adapted to allow flow of the liquid fuel through the grooves and evaporation of the fuel from within the grooves by the flow of air over the said surface, the grooves being disposed at roughly a 45* angle to the axial direction through the prechamber.
Claim 5
Dependent Claim
246 words
A combustion apparatus adapted for use in a gas turbine engine characterized by substantially complete combustion of liquid hydrocarbon fuel and by a low output of nitrogen oxides, the apparatus comprising a combustion liner having a discharge outlet for combustion products at the downstream end of the liner; the liner having an upstream end and liner wall means extending from the upstream end to the downstream end, the wall means enclosing, in sequence from the upstream end to the downstream end, a prechamber, a reaction zone, and a dilution zone, the prechamber including air entrance means at its upstream end effective to direct combustion air with substantial velocity downstream over the inner surface of the prechamber wall means, and liquid fuel introduction means downstream of the said air entrance means disposed to lay a film of liquid fuel on the said inner surface for evaporation by aNd mixture in the prechamber with the said combustion air, wherein the improvement comprises a textured configuration of the said prechamber wall means inner surface defined by a grid of two sets of intersecting grooves in the surface and generally rectangular bosses rising between adjacent grooves adapted to allow flow of the liquid fuel through the grooves and evaporation of the fuel from within the grooves by the flow of air over the said surface, the grooves and bosses being of the order of one-fortieth inch in width and the grooves being of the order of three thousandths inch deep.
Claim 6
Dependent Claim
246 words
A combustion apparatus adapted for use in a gas turbine engine characterized by substantially complete combustion of liquid hydrocarbon fuel and by a low output of nitrogen oxides, the apparatus comprising a combustion liner having a discharge outlet for combustion products at the downstream end of the liner; the liner having an upstream end and liner wall means extending from the upstream end to the downstream end, the wall means enclosing, in sequence from the upstream end to the downstream end, a prechamber, a reaction zone, and a dilution zone, the prechamber including air entrance means at its upstream end effective to direct combustion air with substantial velocity downstream over the inner surface of the prechamber wall means, and liquid fuel introduction means downstream of the said air entrance means disposed to lay a film of liquid fuel on the said inner surface for evaporation by aNd mixture in the prechamber with the said combustion air, wherein the improvement comprises a textured configuration of the said prechamber wall means inner surface defined by a grid of two sets of intersecting grooves in the surface and generally rectangular bosses rising between adjacent grooves adapted to allow flow of the liquid fuel through the grooves and evaporation of the fuel from within the grooves by the flow of air over the said surface, the grooves and bosses being of the order of one-fortieth inch in width and the grooves being of the order of three thousandths inch deep.
References Cited (Backward Citations)
US3075352A
Cited
US3691762A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1978-01-13 | 1978-07-15 | 1979-01-14 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-01-13 | 1982-07-15 | 1983-01-14 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-01-13 | 1986-07-15 | 1987-01-14 | $7700.00 | Window Closed / Lapsed |