# US 7,465,152 B2 · Angel wing seals for turbine blades and methods for selecting stator, rotor and wing seal profiles > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 7,465,152 B2 - Document ID: US7465152B2 - Status: Granted - Kind: B2 - Application number: 11/229,096 - Filed: 2005-09-16 - Published: 2007-09-27 - Granted: 2008-12-16 - Earliest claimed: 2005-09-16 - Assignees: General Electric Company - Inventors: Tagir Robert Nigmatulin - Web page: https://patentgrep.com/patent/US7465152B2 ## CPC - F01D 11/02: by non-contact sealings, e.g. of labyrinth type (for sealing space between rotor blade tips and stator F01D11/08) - F01D 5/20: Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)} - F05D 2250/70: Shape - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - 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 - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract Angel wing seals for turbines are described. In one aspect, an angel wing seal between a rotor blade and nozzle in a turbine inhibits ingestion of hot gas from a hot gas flow through the turbine into turbine wheel spaces. The seal includes, in an example embodiment, a seal body extending from a shank of the blade and generally toward the nozzle. The seal body has at least one concave surface. ## Claims ### Claim 1 In a turbine having a rotor rotatable about an axis, blades carried by said rotor for rotation therewith and nozzles, a seal between a rotor blade and nozzle for inhibiting ingestion of hot gas from a hot gas flow through the turbine into turbine wheel spaces, comprising: a seal body extending from a shank of said blade to a tip and generally toward the nozzle; said seal body comprising a first concave surface defined at said tip, and an outwardly curved surface defined along a length of a body portion extending from the rotor to said tip, said outwardly curved surface is radially inward from said first concave surface and extends outwardly from said seal body. ### Claim 2 (depends on 1) A seal according to claim 1 wherein said seal body further comprises a second concave surface defined along a length of a body portion extending from the rotor to said first concave surface. ### Claim 3 (depends on 1) A seal according to claim 1 wherein the nozzle comprises a first protrusion extending towards the rotor. ### Claim 4 (depends on 1) A seal according to claim 1 wherein the nozzle comprises at least one concave surface. ### Claim 5 (depends on 1) A seal according to claim 1 wherein the rotor comprises at least one protrusion extending outward from said rotor. ### Claim 6 A method for forming a seal arrangement in a turbine having a rotor rotatable about an axis, blades carried by said rotor for rotation therewith and nozzles, an angel wing seal between a rotor blade and nozzle for inhibiting ingestion of hot gas from a hot gas flow through the turbine into turbine wheel spaces, the angel wing seal having a body extending from a shank of the blade to a tip and generally toward the nozzle, said method comprising forming a first concave surface in the angel wing body at the angel wing tip; and forming an outwardly curved surface along a length of a body portion of the angel wing extending from the rotor to the tip, wherein the outwardly curved surface is radially inward from the first concave surface and extends outwardly from the angel wing body. ### Claim 7 (depends on 6) A method according to claim 6 further comprising forming a second concave surface along a length of a body portion extending from the rotor to the first concave surface. ### Claim 8 (depends on 6) A method according to claim 6 further comprising forming a first protrusion extending from the nozzle towards the rotor. ### Claim 9 (depends on 6) A method according to claim 6 further comprising forming at least one concave surface in the nozzle. ### Claim 10 (depends on 6) A method according to claim 6 further comprising forming at least one protrusion extending from the rotor. ### Claim 11 (depends on 6) A method according to claim 6 wherein the concave surface is formed using at least one of casting, machining, welding, coating, and a combination thereof. ### Claim 12 An angel wing seal of a rotor rotatable about an axis in a turbine, blades carried by the rotor for rotation therewith, the turbine further including nozzles, said angel wing seal provided to inhibit ingestion of hot gas from a hot gas flow through the turbine into turbine wheel spaces, said angel wing seal comprising a seal body extending from a shank of said blade to a tip and generally toward the nozzle, said seal body comprising a first concave surface defined at said angel wing tip, and an outwardly curved surface defined along a length of a body portion extending from the rotor to said tip, said outwardly curved surface is radially inward from said first concave surface and extends outwardly from said angel wing body. ### Claim 13 (depends on 12) An angel wing seal according to claim 12 wherein said seal body comprises a second concave surface defined along a length of a body portion extending from the rotor to said first concave surface. ### Claim 14 (depends on 12) An angel wing seal according to claim 12 wherein the nozzle comprises a first protrusion extending towards the rotor, and at least one concave surface. ### Claim 15 (depends on 12) An angel wing seal according to claim 12 wherein the rotor comprises at least one protrusion extending outwardly from the rotor.