US4460313A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Heat shield for radial gas turbine
Assignee: AS KONGSBERG VAPENFABRIK
•
Filing: 1982-03-17
•
Granted: 1984-07-17
•
Expires: 2002-03-17
Abstract
Abstract Two concentric, partially overlapping annular plates mounted on a parallel support plate are provided for partly defining the gas flow path and for shielding bearings, etc. from hot combustion gases in a radial flow gas turbine. The radially outer plate is cooled by compressed air channeled past the plate surface opposite the combustion gases. The compressed air is metered to achieve a temperature distribution decreasing in the radially inward direction for providing sealing contact between the outer edge and the support plate. The radially inner plate is cooled by film cooling using the compressed air exiting the outer plate channel in the vicinity of the overlap.
Inventors
- 👤 Ivar Austrem
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-24 18:15
CPC Classifications
F; F01; F01D; F01D25/00; F01D25/08; F01D25/12; F01D5/00; F01D5/02; F01D5/04; F01D5/043; F01D5/046; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 12
Claim 1
Independent Claim
357 words
Heat shield apparatus for a radial inflow gas turbine, the turbine having a plurality of blades mounted on a hub for rotation about an axis, the combustion gases entering the turbine at an inlet essentially in the radial direction and leaving at an outlet essentially in the axial direction, the apparatus comprising: (a) a first shield member in the form of an annular plate positioned concentric with the hub axis and immediately adjacent the turbine inlet; (b) a second shield member in the form of an annular plate positioned concentric with the hub axis, said second shield member being essentially co-planar with said first shield member and being positioned adjacent to both said first shield member and the hub, said first and second shield members having respective shielding surfaces facing the combustion gas and the turbine outlet and defining, in part, the combustion gas flow path past the turbine blades; (c) means for supporting said first and second shield members; and (d) means cooperating with said support means for cooling said first and second shield members, wherein said support means includes an annular plate member positioned concentric with the hub axis and axially adjacent said first and second shield members, at least some portions of said support plate being spaced from said first shield member, and wherein said cooling means includes (i) a first source of pressurized gas at a low temperature, relative to the combustion gas temperature, and (ii) means for channeling said pressurized low temperature first gas into the space between said first shield member and said support plate for cooling the surface of said first shield member opposite said first shield member shielding surface, and wherein a radially inner edge of said first shield member and an adjacent radially outer edge of said second shield member form an intershield gap, and wherein the heat shield apparatus further includes means for providing a flow path for said pressurized first coolant gas between said first and said second shield members to cooperate with said intershield gap, said first coolant gas flow through said intershield gap for film cooling the shielding surface of said second shield member.
Claim 2
Dependent Claim
357 words
Heat shield apparatus for a radial inflow gas turbine, the turbine having a plurality of blades mounted on a hub for rotation about an axis, the combustion gases entering the turbine at an inlet essentially in the radial direction and leaving at an outlet essentially in the axial direction, the apparatus comprising: (a) a first shield member in the form of an annular plate positioned concentric with the hub axis and immediately adjacent the turbine inlet; (b) a second shield member in the form of an annular plate positioned concentric with the hub axis, said second shield member being essentially co-planar with said first shield member and being positioned adjacent to both said first shield member and the hub, said first and second shield members having respective shielding surfaces facing the combustion gas and the turbine outlet and defining, in part, the combustion gas flow path past the turbine blades; (c) means for supporting said first and second shield members; and (d) means cooperating with said support means for cooling said first and second shield members, wherein said support means includes an annular plate member positioned concentric with the hub axis and axially adjacent said first and second shield members, at least some portions of said support plate being spaced from said first shield member, and wherein said cooling means includes (i) a first source of pressurized gas at a low temperature, relative to the combustion gas temperature, and (ii) means for channeling said pressurized low temperature first gas into the space between said first shield member and said support plate for cooling the surface of said first shield member opposite said first shield member shielding surface, and wherein a radially inner edge of said first shield member and an adjacent radially outer edge of said second shield member form an intershield gap, and wherein the heat shield apparatus further includes means for providing a flow path for said pressurized first coolant gas between said first and said second shield members to cooperate with said intershield gap, said first coolant gas flow through said intershield gap for film cooling the shielding surface of said second shield member.
Claim 3
Dependent Claim
31 words
Heat shield apparatus as in claim 1 wherein means are provided in the space between said first shield member and said support plate for augmenting heat transfer from said opposite surface.
Claim 4
Dependent Claim
54 words
Heat shield apparatus as in claim 2 wherein said heat transfer means includes a plurality of protrusions formed on said opposite surface, the size, location, and number of said protrusions being selected in accordance with the flow rate of said first coolant gas in said coolant space to provide a desired heat transfer coefficient.
Claim 5
Dependent Claim
89 words
Heat shield apparatus as in claim 1 wherein a radially inner edge of said second shield member is spaced from, and forms a gap with, the surface of the rotating hub, the apparatus further including (i) a second source of pressurized coolant gas at a low temperature, relative to the combustion gas temperature, and (ii) means for channeling said second coolant gas through said hub gap, past said second shield member edge, and into the combustion gas flow path for providing film cooling of said second shield member edge.
Claim 6
Dependent Claim
71 words
Heat shield apparatus as in claim 1 wherein a radially outer edge of said first shield member is sealing contacted in the axial direction by said support means around the periphery of said first shield member, and wherein said cooling means provides a first shield member temperature distribution decreasing in the radially inward direction for thermally warping said radially outer edge against said support means to augment the sealing contact force.
Claim 7
Dependent Claim
22 words
Heat shield apparatus as in claim 5 wherein means are provided for flexibly attaching said first shield member to said support means.
Claim 8
Dependent Claim
80 words
Heat shield apparatus as in claim 1 wherein the radially inner edge of said first plate member overlaps the radially outer edge of said second plate member; wherein the first coolant gas used to provide film cooling for said second shield member is channeled to said intershield gap from the space between said first shield member and said support plate; and wherein said feeding means includes channels formed between the overlapped portions of said first and said second shield members.
Claim 9
Dependent Claim
49 words
Heat shield apparatus as in claim 1 wherein said first coolant gas channeling means includes a plurality of holes positioned in the radially outer edge of said support plate for directing jets of said first coolant gas against the portion of said first shield member adjacent the turbine inlet.
Claim 10
Dependent Claim
87 words
Heat shield apparatus as in claim 1 wherein the turbine inlet is defined, in part, by a turbine inlet nozzle support member; wherein said first annular shield member is sized and positioned to have the radially outer edge form a gap with said turbine inlet nozzle support member; and wherein said first pressurized gas source also provides gas flow through said nozzle support gap, past said first shield member outer edge, and into the combustion gas flow path for film cooling said first shield member outer edge.
Claim 11
Dependent Claim
41 words
Heat shield apparatus as in claim 1 wherein said flow path providing means also cooperates with said space between said first shield member and said support plate for flowing said pressurized first coolant gas from said space to said intershield gap.
Claim 12
Dependent Claim
44 words
Heat shield apparatus as in claim 1 wherein said adjacent edges of said first and said second shield members are overlapped to form said intershield gap, and wherein said flow path providing means includes channels formed in at least one of said overlapped edges.
References Cited (Backward Citations)
US2440069A
Cited
US3167301A
Cited
US3893786A
Cited
US3849022A
Cited
US4017207A
Cited
US4053254A
Cited
US4083649A
Cited
US4101241A
Cited
US4157881A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1987-07-17 | 1988-01-16 | 1988-07-17 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1991-07-17 | 1992-01-16 | 1992-07-17 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1995-07-17 | 1996-01-16 | 1996-07-17 | $7700.00 | Window Closed / Lapsed |