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US 5,169,287 AGranted
Shroud cooling assembly for gas turbine engine
AssigneeGeneral Electric Company
InventorsRobert Proctor, Larry W. Plemmons, Gulcharan S. Brainch, John R. Hess, Robert J. Albers
Life of this patent
Estimating the term…
Abstract
To cool the shroud in the high pressure turbine section of a gas turbine engine, high pressure cooling air is directed in metered flow to baffle plenums and thence through baffle perforations to impingement cool the shroud rails and back surface. Impingement cooling air then flows through elongated, convection cooling passages in the shroud and exits to flow along the shroud front surface with the main gas stream to provide film cooling. The baffle perforations and the convection cooling passages are interactively located to achieve maximum cooling benefit and highly efficient cooling air utilization.
Claims14
A shroud cooling assembly for a gas turbine engine comprising, in combination:
- A. a plurality of arcuate shroud sections circumferentially arranged to surround the rotor blades of a high pressure turbine in the gas turbine engine, each said shroud section including
- 1) a base having a radially outer back surface, a radially inner front surface defining a portion of a radially outer boundary for the engine main gas stream flowing through the high pressure turbine, an upstream end and a downstream end,
- 2) a fore rail extending radially outwardly from said base adjacent said upstream end thereof,
- 3) an aft rail extending radially outwardly from said base adjacent said downstream end thereof,
- 4) a pair of spaced side rails extending radially outwardly from said base in conjoined relation with said fore and aft rails, and
- 5) a plurality of convection cooling passages extending through said base with inlets at said base back surface and outlets at said base front surface, said cooling passages having lengths greatly exceeding the thickness of said base between said back and front surfaces thereof,
- B. a plurality of arcuate hanger sections secured to the outer case of the gas turbine engine for supporting said shroud sections, each said hanger section including at least one hole therethrough for metering the flow of pressurized cooling air from a nozzle plenum, each said hanger section defining with said base back surface and said fore, aft and side rails of each said shroud section a shroud chamber;
- C. a pan-shaped baffle affixed to each said hanger section in position in within each said shroud chamber to define with said hanger section a baffle plenum in communication with said metering hole to receive pressurized cooling air directly from said nozzle plenum, said baffle including a plurality of perforations through which streams of cooling air are radially inwardly directed into impingement with one of said shroud sections, the positions of said perforations being such that said cooling air streams impinge only on said base back surface at locations intermediate said convection cooling passage inlets, whereby to maximize impingement cooling of said shroud sections, the impingement cooing air then flowing through said passages to convection cool said shroud sections and ultimately flowing along said shroud front surface to provide film cooling of said shroud sections;
- and
- D. wherein said passages are interactively arranged in groups, said groups including first, second and third rows, such that said passage inlets of said first row are substantially radially aligned with said passage outlets of said second row, whereby to compensate for the characteristics of decreasing convection heat transfer coefficient as cooling air flows through said passages from said inlets to said outlets.
7 more elements
The shroud cooling assembly for a gas turbine engine comprising, in combination:
- A. a plurality of arcuate shroud sections circumferentially arranged to surround the rotor blades of a high pressure turbine in the gas turbine engine, each said shroud section including
- 1) a base having a radially outer back shroud section including inner front surface defining a portion of a radially outer boundary for the engine main gas stream flowing through the high pressure turbine, an upstream end and a downstream end,
- 2) a fore rail extending radially outwardly from said base adjacent said upstream end thereof,
- 3) an aft rail extending radially outwardly from said base adjacent said downstream end thereof,
- 4) a pair of spaced side rails extending radially outwardly from said base in conjoined relation with said fore and aft rails, said fore, aft and side rails framing a portion of said base substantially radially aligned with the turbine blades, and
- 5) a plurality of convection cooling passages extending through said base, said cooling passages having lengths greatly exceeding the thickness of said base between said back and front surfaces thereof,
- B. a plurality of arcuate hanger sections secured to the outer case of the gas turbine engine for supporting said shroud sections, each said hanger section including at least one hole therethrough for metering the flow of pressurized cooling air from a nozzle plenum, each said hanger section defining with said base back surface and said fore, aft and side rails of each said shroud section a shroud chamber;
- C. a pan-shaped baffle affixed to each said hanger section in position with each said shroud chamber to define with said hanger section a baffle plenum in communication with said metering hole to receive pressurized cooling air directly from said nozzle plenum, said baffle including a first plurality of perforations positioned to direct streams of cooling air into impingement with said fore, aft and side rails at substantially uniformly distributed locations and a second plurality of perforations through which streams of cooling air are directed into impingement with said back surface of said portion of said base framed by said rails to concentrate impingement shroud cooling thereat, the rail and base impingement cooling air then flowing through said passages to convection cool said shroud sections and ultimately flowing along said shroud radially inner surface to provide film cooling of said shroud sections:
- D. wherein said passages have inlets at said back surface of said framed base portion, the positions of said plurality of perforations being such that the airstreams therefrom impinge only on said base back surface ate areas intermediate said passage inlets;
- and
- E. wherein said passages are interactively arranged in groups, said groups including first, second and third rows, such that said passage inlets of said first row are substantially radially aligned with said passage outlets of said second row, whereby to compensate for the characteristic of decreasing convection heat transfer coefficient as cooling air flows through said passages from said inlets to said outlets.
8 more elements
Dependencies are inferred from the claim text.