# US 10,502,077 B2 · Vane retainer > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,502,077 B2 - Document ID: US10502077B2 - Status: Granted - Kind: B2 - Application number: 15/073,008 - Filed: 2016-03-17 - Published: 2017-09-21 - Granted: 2019-12-10 - Earliest claimed: 2016-03-17 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Edward Torres - Web page: https://patentgrep.com/patent/US10502077B2 ## CPC - F01D 9/042: {fixing blades to stators (fixing stator-rings in the casing or to each other F01D25/246)} - F01D 17/162: {for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence)} - F02C 9/20: by throttling; by adjusting vanes - F04D 29/323: {adjustable} - F04D 29/54: Fluid-guiding means, e.g. diffusers - F05D 2220/32: in gas turbines - F05D 2220/3217: for the first stage of a compressor or a low pressure compressor - F05D 2240/12: Fluid guiding means, e.g. vanes - F05D 2240/14: Casings or housings protecting or supporting assemblies within - F05D 2250/181: ridged - F05D 2250/182: crenellated, notched - F05D 2260/31: Retaining bolts or nuts - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A vane retainer for a gas turbine engine includes a retainer body, an inner surface of the retainer body to engage complimentary threads of a mating component, and a plurality of castellations located at an end of the retainer body for engagement with complementary installation tool features during installation of the vane retainer to the mating component. A gas turbine engine includes a combustor and a plurality of vane assemblies in fluid communication with the combustor. Each vane assembly includes a vane having an airfoil portion and a vane stem extending from the airfoil portion. The vane stem is inserted into a bushing. A vane retainer is engaged with the bushing and includes a retainer body, an inner surface of the retainer body to engage complimentary threads of the bushing, and a plurality of castellations located at an end of the retainer body for engagement with complementary installation tool features. ## Claims ### Claim 1 A vane retainer for a gas turbine engine comprising: a retainer body; a threaded inner surface of the retainer body configured to engage complimentary threads of an outer surface of a bushing installed to a casing, the bushing receptive of a vane stem; and a plurality of castellations disposed at a distal end of the retainer body for engagement with complementary installation tool features during installation of the vane retainer to the bushing. ### Claim 2 (depends on 1) The vane retainer of claim 1, wherein the plurality of castellations are equally spaced about a vane retainer axis. ### Claim 3 (depends on 1) The vane retainer of claim 1, wherein a castellation height is substantially equal to a castellation width. ### Claim 4 (depends on 1) The vane retainer of claim 1 further comprising a chamfer disposed at a top surface of the castellation. ### Claim 5 (depends on 1) The vane retainer of claim 1, further comprising a fillet disposed at a castellation base. ### Claim 6 (depends on 1) The vane retainer of claim 1, wherein the plurality of castellations is eight equally sized castellations. ### Claim 7 A vane assembly for a gas turbine engine, comprising: a vane having: an airfoil portion; and a vane stem extending from the airfoil portion; a bushing into which the vane stem is inserted, a vane stem outer surface abutting a bushing inner surface; and a vane retainer engaged with the bushing at a bushing outer surface, including: a retainer body; a threaded inner surface of the retainer body to engage complimentary threads of the bushing; and a plurality of castellations disposed at a distal end of the retainer body for engagement with complementary installation tool features during installation of the vane retainer to the bushing. ### Claim 8 (depends on 7) The vane assembly of claim 7, wherein the plurality of castellations are equally spaced about a vane retainer axis. ### Claim 9 (depends on 7) The vane assembly of claim 7, wherein a castellation height is substantially equal to a castellation width. ### Claim 10 (depends on 7) The vane assembly of claim 7, further comprising a chamfer disposed at a top surface of the castellation. ### Claim 11 (depends on 7) The vane assembly of claim 7, further comprising a fillet disposed at a castellation base. ### Claim 12 (depends on 7) The vane assembly of claim 7, wherein the plurality of castellations is eight equally sized castellations. ### Claim 13 (depends on 7) The vane assembly of claim 7, wherein the vane stem defines an axis of rotation of the vane. ### Claim 14 A gas turbine engine, comprising: a combustor; and a plurality of vane assemblies in fluid communication with the combustor, each vane assembly including: a vane having: an airfoil portion; and a vane stem extending from the airfoil portion; a bushing into which the vane stem is inserted, a vane stem outer surface abutting a bushing inner surface; and a vane retainer engaged with the bushing at a bushing outer surface, including: a retainer body; a threaded inner surface of the retainer body to engage complimentary threads of the bushing; and a plurality of castellations disposed at a distal end of the retainer body for engagement with complementary installation tool features during installation of the vane retainer to the bushing. ### Claim 15 (depends on 14) The gas turbine engine of claim 14, wherein the plurality of castellations are equally spaced about a vane retainer axis. ### Claim 16 (depends on 14) The gas turbine engine of claim 14, wherein a castellation height is substantially equal to a castellation width. ### Claim 17 (depends on 14) The gas turbine engine of claim 14, further comprising a chamfer disposed at a top surface of the castellation. ### Claim 18 (depends on 14) The gas turbine engine of claim 14, further comprising a fillet disposed at a castellation base. ### Claim 19 (depends on 14) The gas turbine engine of claim 14, wherein the plurality of castellations is eight equally sized castellations.