# US 11,111,802 B2 · 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 11,111,802 B2 - Document ID: US11111802B2 - Status: Granted - Kind: B2 - Application number: 16/400,618 - Filed: 2019-05-01 - Published: 2020-11-05 - Granted: 2021-09-07 - Earliest claimed: 2019-05-01 - Assignees: Raytheon Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Tracy A. Propheter-Hinckley; Egon Salimusaj - Web page: https://patentgrep.com/patent/US11111802B2 ## CPC - F01D 11/001: {for sealing space between stator blade and rotor} - F01D 11/005: {Sealing means between non relatively rotating elements} - F01D 9/042: {fixing blades to stators (fixing stator-rings in the casing or to each other F01D25/246)} - F01D 11/003: {by packing rings; Mechanical seals} - F01D 11/006: {Sealing the gap between rotor blades or blades and rotor} - F01D 25/246: {Fastening of diaphragms or stator-rings} - B24B 19/02: for grinding grooves, e.g. on shafts, in casings, in tubes, homokinetic joint elements - F05D 2230/10: by removing material - F05D 2230/60: Assembly methods - F05D 2240/57: Leaf seals - F05D 2240/80: Platforms for stationary or moving blades - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - B24B: MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING (grinding of gear teeth B23F, of screw-threads B23G1/36; by electro-erosion B23H; abrasive or related blasting B24C; tools for grinding, buffing or sharpening B24D; polishing compositions C09G1/00; abrasives C09K3/14; electrolytic etching or polishing C25F3/00; grinding arrangements for use on assembled railway tracks E01B31/17); DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A component for a gas turbine engine includes a first platform that has a first pair of circumferential surfaces and a first axially aft surface. A first axially extending seal slot is located in each of the first pair of circumferential surfaces and the first axially aft surface. A first cover plate is attached to the first axially aft surface and encloses at least a portion of the first axially extending seal slots. ## Claims ### Claim 1 A component for a gas turbine engine comprising: a first platform having a first pair of circumferential surfaces that are circumferentially opposing, a first axially aft surface, and a surface defining a core gas flow path; a first axially extending seal slot located in each of the first pair of circumferential surfaces and the first axially aft surface; and a first cover plate attached to the first axially aft surface enclosing at least a portion of the first axially extending seal slot located in each of the first pair of circumferential surfaces, wherein a radial direction and a circumferential direction are defined with respect to a central longitudinal axis of the gas turbine engine. ### Claim 2 (depends on 1) The component of claim 1, wherein the first axially aft surface intersects the pair of circumferential surfaces. ### Claim 3 (depends on 1) The component of claim 1, wherein the first axially extending seal slots are formed with a grinding process. ### Claim 4 (depends on 1) The component of claim 1, wherein the first cover plate is welded to the first axially aft surface. ### Claim 5 (depends on 4) The component of claim 4, wherein the first axially extending seal slots extend through a leading edge of the first platform. ### Claim 6 (depends on 1) The component of claim 1, wherein a portion of the first axially aft surface defines a trailing edge rail and the axially aft surface intersects the pair of circumferential surfaces and the component includes one of a blade outer air seal or an airfoil. ### Claim 7 (depends on 6) The component of claim 6, wherein the component is an airfoil and includes a first airfoil end adjacent the first platform and a second airfoil end adjacent a second platform having a second pair of circumferential surfaces and a second axially aft surface and a second axially extending seal slot located in each of the second pair of circumferential surfaces and the second axially aft surface. ### Claim 8 (depends on 7) The component of claim 7, including a second cover plate attached to the second axially aft surface enclosing at least a portion of the second axially extending seal slots. ### Claim 9 A gas turbine engine comprising: a compressor section upstream of a combustor section; and a turbine section downstream of the combustor section wherein at least one of the compressor section or the turbine section includes a component having: a first platform having a first pair of circumferential surfaces that are circumferentially opposing and a first axially aft surface; a first axially extending seal slot located in each of the first pair of circumferential surfaces and the first axially aft surface; and a first cover plate attached to the first axially aft surface enclosing at least a portion of the first axially extending seal slot located in each of the first pair of circumferential surfaces; an airfoil having a first end adjacent the first platform and a second end adjacent a second platform, the second platform having a second pair of opposing circumferential surfaces and a second axially aft surface and a second axially extending seal slot located in each of the second pair of circumferential surfaces and the second axially aft surface, wherein a radial direction and a circumferential direction are defined with respect to a central longitudinal axis of the gas turbine engine. ### Claim 10 (depends on 9) The gas turbine engine of claim 9, wherein the first axially aft surface intersects the pair of circumferential surfaces. ### Claim 11 (depends on 9) The gas turbine engine of claim 9, wherein the first axially extending seal slots are formed with a grinding process. ### Claim 12 (depends on 9) The gas turbine engine of claim 9, wherein the first cover plate is welded to the first axially aft surface. ### Claim 13 (depends on 12) The gas turbine engine of claim 12, wherein the first axially extending seal slot extends through a leading edge of the first platform. ### Claim 14 (depends on 9) The gas turbine engine of claim 9, including a second cover plate attached to the second axially aft surface enclosing at least a portion of the second axially extending seal slots. ### Claim 15 A method of forming a seal slot in a component including the steps of: forming a first axially extending seal slot through each of a pair of first circumferential surfaces and through a first axially aft surface on a first platform, wherein the pair of first circumferential surfaces are circumferentially opposed, the first platform includes a surface defining a core flow path, and a circumferential direction is defined with respect to a central longitudinal axis of a gas turbine engine; and enclosing a portion of the first axially extending seal slot located in each of the pair of first circumferential surfaces with a cover plate attached to the first axially aft surface. ### Claim 16 (depends on 15) The method of claim 15, wherein the first axially extending seal slot located in each of the pair of first circumferential surfaces is formed through a grinding process. ### Claim 17 (depends on 15) The method of claim 15, further comprising the steps of: forming a second axially extending seal slot through each of a pair of second circumferential surfaces and a second axially aft surface on a second platform, wherein the pair of second circumferential surfaces are circumferentially opposed, an airfoil includes a first end adjacent the first platform and a second end adjacent the second platform; and enclosing at least a portion of the pair of second axially extending seal slot, with a second cover plate attached to the second axially aft surface. ### Claim 18 (depends on 17) The method of claim 17, wherein the second axially extending seal slot is formed through a grinding process. ### Claim 19 (depends on 18) The method of claim 18, including welding the second cover plate to the first axially aft surface.