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US 10,240,476 B2Granted
Full hoop blade track with interstage cooling air
AssigneesRolls-Royce North American Technologies Inc., ROLLS-ROYCE plc
InventorsBruce E. Varney, Jack D. Petty, Daniel K. Vetters, Eugene Clemens
Life of this patent
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Abstract
A gas turbine engine includes a turbine having a plurality of vanes, a plurality of blades, a turbine shroud arranged around the vanes and blades, and a turbine case arranged around the turbine shroud. The turbine shroud is sized to block combustion products from passing over the blades without pushing the blades to rotate. The turbine shroud includes a runner arranged around the blades and a carrier arranged around the runner.
Claims15
A turbine shroud for use in a gas turbine engine having a central axis, the turbine shroud comprising
- an annular carrier formed to define a radially inwardly-opening carrier channel that extends around the central axis and the annular carrier includes an outer pin receiver that extends through the annular carrier and opens into the carrier channel to allow pressurized cooling air to pass through the annular carrier into the carrier channel and a high-pressure cooling air passageway that extends radially through the annular carrier,
- a one-piece annular runner aligned axially with the carrier channel of the annular carrier, the one-piece annular runner includes an inner radial runner surface located radially between the annular carrier and the central axis and an outer radial runner surface located radially between the inner radial runner surface and the annular carrier, and the outer radial runner surface cooperates with the annular carrier to form an annular buffer chamber between the annular carrier and the one-piece annular runner, and
- a cooling system including an annular impingement plate positioned in the annular buffer chamber to separate the annular buffer chamber into an outer chamber and an inner chamber located radially between the outer chamber and the one-piece annular runner, the outer pin receiver opens into the outer chamber to direct the pressurized cooling air into the outer chamber, and the annular impingement plate includes a plurality of diffusion holes spaced circumferentially around the annular impingement plate and each diffusion hole extends radially through the impingement plate to direct the pressurized cooling air in the outer chamber through the annular impingement plate into the inner chamber and toward the outer radial runner surface of the one-piece annular runner,
- wherein the one-piece annular runner includes a forward section, an aft section spaced apart axially from the forward section, and a midsection extending between the forward section and the aft section, the high-pressure cooling air passageway is configured to direct high-pressure air toward the forward section of the one-piece annular runner, the high-pressure air has a greater pressure than the pressurized cooling air, and the turbine shroud further includes a first seal positioned radially between the one-piece annular runner and the annular carrier and positioned axially between the high-pressure cooling air passageway and the annular buffer chamber.
1 more element
A gas turbine engine comprising
- a turbine case arranged around a central axis of the gas turbine engine, the turbine case includes one or more outer keyways that extend through the turbine case,
- a turbine shroud including (i) a carrier formed to define a radially inwardly-opening carrier channel that extends around the central axis and one or more outer pin receivers that extend through the carrier and open into the carrier channel and (ii) an annular runner aligned axially with the carrier and positioned to close the inwardly-opening carrier channel to form an annular buffer chamber between the carrier and the annular runner, and
- a cooling system including one or more hollow outer insert pins that extend through the corresponding one or more outer keyways formed in the turbine case and the one or more outer pin receivers formed in the carrier into the buffer chamber to allow pressurized cooling air to pass through the turbine case and the carrier into the buffer chamber,
- wherein the annular runner includes a forward section, an aft section spaced apart axially from the forward section, and a midsection extending between the forward section and the aft section, the carrier is formed to include a high-pressure cooling air passageway that extends through the carrier and is configured to direct high-pressure air toward the forward section of the annular runner, and the high-pressure air has a greater pressure than the pressurized cooling air,
- wherein the gas turbine engine further includes a first seal positioned radially between the annular runner and the carrier and positioned axially between the high-pressure cooling air passageway and the buffer chamber.
2 more elements
Dependencies are inferred from the claim text.