# US 2011/0236188 A1 · Blade outer seal for a gas turbine engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2011/0236188 A1 - Document ID: US20110236188A1 - Status: Published application - Kind: A1 - Application number: 12/732,958 - Filed: 2010-03-26 - Published: 2011-09-29 - Earliest claimed: 2010-03-26 - Assignees: United Technologies Corporation - Inventors: James N. Knapp; Paul M. Lutjen; Susan M. Tholen - Web page: https://patentgrep.com/patent/US20110236188A1 ## CPC - F01D 11/10: using sealing fluid, e.g. steam - F01D 5/20: Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)} - F05D 2240/11: Shroud seal segments - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A blade outer air seal for a gas turbine engine is provided. The blade outer air seal includes a body having an outer radial surface, an inner radial surface, and a plurality of cooling air apertures. The body extends between a forward edge and an aft edge. The inner radial surface includes at least one first seal section, at least one second seal section, and a riser extending radially between the first seal section and the second seal section. Each of the plurality of cooling air apertures extends between the outer radial surface and the riser, and each cooling air aperture has an exit configured to direct cooling air substantially parallel to the second seal section of the inner radial surface. ## Claims ### Claim 1 A blade outer air seal for a gas turbine engine, comprising: a body extending between a forward edge and an aft edge, and including: an outer radial surface; an inner radial surface including at least one first seal section, at least one second seal section, and a riser extending radially between the first seal section and the second seal section; and a plurality of cooling air apertures, where each cooling air aperture extends between the outer radial surface and the riser, and where each cooling air aperture has an exit configured to direct cooling air substantially parallel to the second seal section of the inner radial surface. ### Claim 2 (depends on 1) The blade outer air seal of claim 1, wherein the body includes a plurality of first seal sections, a plurality of second seal sections, and a plurality of risers, and wherein each riser extends radially between one of the first seal sections and one of the second seal sections; and wherein cooling air apertures extend between the outer radial surface and each riser, and wherein the exit of each cooling air aperture is configured to direct cooling air substantially parallel to the respective second seal section of the inner radial surface. ### Claim 3 (depends on 1) The blade outer air seal of claim 1, wherein: the inner radial surface further includes a second riser extending radially between the second seal section and a third seal section; and the body further includes a plurality of second cooling air apertures, wherein each second cooling air aperture extends between the outer radial surface and the second riser, and wherein each second cooling air aperture has an exit configured to direct cooling air substantially parallel to the third seal section of the inner radial surface. ### Claim 4 (depends on 3) The blade outer air seal of claim 3, wherein the body further includes a plurality of third cooling air apertures that extend between the outer radial surface and the aft edge of the body. ### Claim 5 (depends on 3) The blade outer air seal of claim 3, wherein at least portions of the cooling air apertures and the second cooling air apertures are axially aligned in a stacked configuration. ### Claim 6 (depends on 1) The blade outer air seal of claim 1, wherein the exit of at least one of the cooling air apertures includes a diffuser portion. ### Claim 7 (depends on 1) The blade outer air seal of claim 1, wherein the body includes at least one circumferentially extending passage in fluid communication with one or more of the cooling air apertures. ### Claim 8 A gas turbine engine, comprising: an engine case; a rotor stage having a plurality of blades; and a blade outer air seal disposed between the engine case and the blades, which blade outer air seal comprises a body that extends between a forward edge and an aft edge, and includes: an outer radial surface; an inner radial surface that has at least one first seal section, at least one second seal section, and a riser extending radially between the first seal section and the second seal section; and a plurality of cooling air apertures, where each cooling air aperture extends between the outer radial surface and the riser, and where each cooling air aperture has an exit configured to direct cooling air substantially parallel to the second seal section of the inner radial surface. ### Claim 9 (depends on 8) The engine of claim 8, wherein the body includes a plurality of first seal sections, a plurality of second seal sections, and a plurality of risers, and wherein each riser extends radially between one of the first seal sections and one of the second seal sections; and wherein cooling air apertures extend between the outer radial surface and each riser, and wherein the exit of each cooling air aperture is configured to direct cooling air substantially parallel to the respective second seal section of the inner radial surface. ### Claim 10 (depends on 8) The engine of claim 8, wherein: the inner radial surface further includes a second riser extending radially between the second seal section and a third seal section; and the body further includes a plurality of second cooling air apertures, wherein each second cooling air aperture extends between the outer radial surface and the second riser, and wherein each second cooling air aperture has an exit configured to direct cooling air substantially parallel to the third seal section of the inner radial surface. ### Claim 11 (depends on 10) The engine of claim 10, wherein the body further includes a plurality of third cooling air apertures that extend between the outer radial surface and the aft edge of the body. ### Claim 12 (depends on 10) The blade outer air seal of claim 10, wherein at least portions of the cooling air apertures and the second cooling air apertures are axially aligned in a stacked configuration. ### Claim 13 (depends on 8) The engine of claim 8, wherein the exit of at least one of the cooling air apertures includes a diffuser portion. ### Claim 14 (depends on 8) The engine of claim 8, wherein the body includes at least one circumferentially extending passage in fluid communication with one or more of the cooling air apertures. ### Claim 15 (depends on 8) The engine of claim 8, wherein the blades have a tip geometry that substantially mates with a geometry of the inner radial surface of the blade outer air seal body.