US3877221A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Combustion apparatus air supply
Assignee: Motors Liquidation Co
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Filing: 1973-08-27
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Granted: 1975-04-15
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Expires: 1993-08-27
Abstract
Abstract An improvement in diffusers to guide air flow from the compressor of a gas turbine engine into the combustion apparatus, splitting the air between front, outer, and inner walls of the combustion liner. A slot in a wall of the diffuser transfers air from compressor mid-radius to the passage leading to the liner inner wall.
Inventors
- 👤 Arthur H Lefebvre
- 👤 Harold L Stocker
- 👤 Samuel B Reider
- 👤 Jerry G Tomlinson
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-25 08:55
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/02; F23R3/04; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
287 words
In a gas turbine engine comprising a compressor with an annular axial outlet, outer and inner casing walls defining an annular combustion space connected to the outlet, and an annular combustion liner disposed between the said casing walls, the casing walls having forward portions diverging to define a diffusing zone beginning at the compressor outlet, the combustion liner having an upstream wall and outer and inner walls with openings for entrance of air into the liner in each of the said liner walls, the improvement comprising an airflow dividing diffuser disposed in the diffusing zone and connected to the upstream end of the liner, the diffuser having a snout providing an annular entrance adjacent the compressor outlet and at a midradius of the outlet, an outer diffuser wall extending from the snout to the outer wall of the liner, and an inner diffuser wall extending from the snout to the inner wall of the liner; the said diffuser walls bounding a diffusing flow path to the upstream liner wall and defining with the upstream liner wall an air space, the outer diffuser wall and outer casing wall defining a diffusing flow path to the outer liner wall, the outer diffuser wall blocking flow between the said air space and the outer liner wall, and the inner casing wall defining a diffusing flow path to the inner liner wall; the said diffusing flow paths taking air from the outer, central, and inner annular zones of the compressor outlet, respectively; and the diffuser defining means for diverting a portion of the air from the path leading to the upstream liner wall into the path leading to the inner liner wall responsive to relative pressure conditions in the said paths.
Claim 2
Dependent Claim
287 words
In a gas turbine engine comprising a compressor with an annular axial outlet, outer and inner casing walls defining an annular combustion space connected to the outlet, and an annular combustion liner disposed between the said casing walls, the casing walls having forward portions diverging to define a diffusing zone beginning at the compressor outlet, the combustion liner having an upstream wall and outer and inner walls with openings for entrance of air into the liner in each of the said liner walls, the improvement comprising an airflow dividing diffuser disposed in the diffusing zone and connected to the upstream end of the liner, the diffuser having a snout providing an annular entrance adjacent the compressor outlet and at a midradius of the outlet, an outer diffuser wall extending from the snout to the outer wall of the liner, and an inner diffuser wall extending from the snout to the inner wall of the liner; the said diffuser walls bounding a diffusing flow path to the upstream liner wall and defining with the upstream liner wall an air space, the outer diffuser wall and outer casing wall defining a diffusing flow path to the outer liner wall, the outer diffuser wall blocking flow between the said air space and the outer liner wall, and the inner casing wall defining a diffusing flow path to the inner liner wall; the said diffusing flow paths taking air from the outer, central, and inner annular zones of the compressor outlet, respectively; and the diffuser defining means for diverting a portion of the air from the path leading to the upstream liner wall into the path leading to the inner liner wall responsive to relative pressure conditions in the said paths.
Claim 3
Dependent Claim
293 words
In a gas turbine engine comprising a compressor with an annular axial outlet, outer and inner casing walls defining an annular combustion space connected to the outlet, and an annular combustion liner disposed between the said casing walls, the casing walls having forward portions diverging to define a diffusing zone beginning at the compressor outlet, the combustion liner having an upstream wall and outer and inner walls with openings for entrance of air into the liner in each of the said liner walls, the improvement comprising an airflow dividing diffuser disposed in the diffusing zone and connected to the upstream end of the liner, the diffuser having a snout providing an annular entrance adjacent the compressor outlet and at a mid-radius of the outlet, an outer diffuser wall extending from the snout to the outer wall of the liner, and an inner diffuser wall extending from the snout to the inner wall of the liner; the said diffuser walls bounding a diffusing flow path to the upstream liner wall and defining with the upstream liner wall an air space, the outer diffuser wall and outer casing wall defining a diffusing flow path to the outer liner wall, the outer diffuser wall blocking flow between the said air space and the outer liner wall, and the inner casing wall defining a diffusing flow path to the inner liner wall; the said diffusing flow paths taking air from the outer, central, and inner annular zones of the compressor outlet, respectively; and the inner diffuser wall defining circumferentially extending slot means for diverting a portion of the air from the path leading to the upstream liner wall iNto the path leading to the inner liner wall in response to relative pressure conditions in the said paths.
Claim 4
Dependent Claim
293 words
In a gas turbine engine comprising a compressor with an annular axial outlet, outer and inner casing walls defining an annular combustion space connected to the outlet, and an annular combustion liner disposed between the said casing walls, the casing walls having forward portions diverging to define a diffusing zone beginning at the compressor outlet, the combustion liner having an upstream wall and outer and inner walls with openings for entrance of air into the liner in each of the said liner walls, the improvement comprising an airflow dividing diffuser disposed in the diffusing zone and connected to the upstream end of the liner, the diffuser having a snout providing an annular entrance adjacent the compressor outlet and at a mid-radius of the outlet, an outer diffuser wall extending from the snout to the outer wall of the liner, and an inner diffuser wall extending from the snout to the inner wall of the liner; the said diffuser walls bounding a diffusing flow path to the upstream liner wall and defining with the upstream liner wall an air space, the outer diffuser wall and outer casing wall defining a diffusing flow path to the outer liner wall, the outer diffuser wall blocking flow between the said air space and the outer liner wall, and the inner casing wall defining a diffusing flow path to the inner liner wall; the said diffusing flow paths taking air from the outer, central, and inner annular zones of the compressor outlet, respectively; and the inner diffuser wall defining circumferentially extending slot means for diverting a portion of the air from the path leading to the upstream liner wall iNto the path leading to the inner liner wall in response to relative pressure conditions in the said paths.
Claim 5
Dependent Claim
329 words
In a gas turbine engine comprising a compressor with an annular axial outlet, outer and inner casing walls defining an annular combustion space connected to the outlet, and an annular combustion liner disposed between the said casing walls, the casing walls having forward portions diverging to define a diffusing zone beginning at the compressor outlet, the combustion liner having an upstream wall and outer and inner walls with openings for entrance of air into the liner in each of the said liner walls, the improvement comprising an airflow dividing diffuser disposed in the diffusing zone and connected to the upstream end of the liner, the diffuser having a snout providing an annular entrance adjacent the compressor outlet and at a mid-radius of the outlet, an outer diffuser wall extending from the snout to the outer wall of the liner, and an inner diffuser wall extending from the snout to the inner wall of the liner; the said diffuser walls bounding a diffusing flow path to the upstream liner wall and defining with the upstream liner wall an air space, the outer diffuser wall and outer casing wall defining a diffusing flow path to the outer liner wall, the outer diffuser wall blocking flow between the said air space and the outer liner wall, and the inner casing wall defining a diffusing flow path to the inner liner wall; the said diffusing flow paths taking air from the outer, central, and inner annular zones of the compressor outlet, respectively; the inner diffuser wall defining circumferentially extending slot means for diverting a portion of the air from the path leading to the upstream liner wall into the path leading to the inner liner wall in response to relative pressure conditions in the said paths; and the diffusing flow path to the upstream liner wall being disposed to discharge the air into the said air space in a direction more predominantly toward the inner diffuser wall than toward the outer diffuser wall.
Claim 6
Dependent Claim
329 words
In a gas turbine engine comprising a compressor with an annular axial outlet, outer and inner casing walls defining an annular combustion space connected to the outlet, and an annular combustion liner disposed between the said casing walls, the casing walls having forward portions diverging to define a diffusing zone beginning at the compressor outlet, the combustion liner having an upstream wall and outer and inner walls with openings for entrance of air into the liner in each of the said liner walls, the improvement comprising an airflow dividing diffuser disposed in the diffusing zone and connected to the upstream end of the liner, the diffuser having a snout providing an annular entrance adjacent the compressor outlet and at a mid-radius of the outlet, an outer diffuser wall extending from the snout to the outer wall of the liner, and an inner diffuser wall extending from the snout to the inner wall of the liner; the said diffuser walls bounding a diffusing flow path to the upstream liner wall and defining with the upstream liner wall an air space, the outer diffuser wall and outer casing wall defining a diffusing flow path to the outer liner wall, the outer diffuser wall blocking flow between the said air space and the outer liner wall, and the inner casing wall defining a diffusing flow path to the inner liner wall; the said diffusing flow paths taking air from the outer, central, and inner annular zones of the compressor outlet, respectively; the inner diffuser wall defining circumferentially extending slot means for diverting a portion of the air from the path leading to the upstream liner wall into the path leading to the inner liner wall in response to relative pressure conditions in the said paths; and the diffusing flow path to the upstream liner wall being disposed to discharge the air into the said air space in a direction more predominantly toward the inner diffuser wall than toward the outer diffuser wall.
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) | 1978-04-14 | 1978-10-14 | 1979-04-15 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-04-14 | 1982-10-14 | 1983-04-15 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-04-14 | 1986-10-14 | 1987-04-15 | $7700.00 | Window Closed / Lapsed |