# US 10,767,503 B2 · Stator assembly with retention clip for 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 10,767,503 B2 - Document ID: US10767503B2 - Status: Granted - Kind: B2 - Application number: 15/618,903 - Filed: 2017-06-09 - Published: 2018-12-13 - Granted: 2020-09-08 - Earliest claimed: 2017-06-09 - Assignees: Raytheon Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Brian Barainca; Gary F. Fowler - Web page: https://patentgrep.com/patent/US10767503B2 ## CPC - F01D 9/042: {fixing blades to stators (fixing stator-rings in the casing or to each other F01D25/246)} - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F02C 3/04: having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) - F02K 3/06: with front fan - F05D 2230/60: Assembly methods - F05D 2240/12: Fluid guiding means, e.g. vanes - F05D 2260/30: Retaining components in desired mutual position - 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) - 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) - F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00) - 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 A stator assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a first shroud that extends about an axis to bound a flow path. The first shroud defines a first shroud opening. An airfoil has an airfoil body that extends from a first end portion. The first end portion is received in the first shroud opening and defines a retention aperture. A retention clip includes a body and at least one locking feature. The body extends between opposed clip end portions. The at least one locking feature is compressibly received through the retention aperture, and the least one locking feature is decompressible from the body to define a ramp sloping towards one of the clip end portions to limit movement of the airfoil relative to the first shroud when in the installed position. ## Claims ### Claim 1 A stator assembly for a gas turbine engine comprising: a first shroud extending about an axis to bound a flow path, the first shroud defining a first shroud opening; an airfoil including an airfoil body extending from a first end portion, the first end portion received in the first shroud opening and defining a retention aperture; and a retention clip including a body and at least one locking feature extending from the body, the body extending between opposed clip end portions and between opposed sidewalls that cooperate to establish a perimeter of the body, the at least one locking feature compressibly received through the retention aperture, and the at least one locking feature decompressible from the body to define a ramp sloping towards one of the clip end portions to limit movement of the airfoil relative to the first shroud when in the installed position; and wherein the at least one locking feature is an elongated tab having a terminal end that abuts against an external wall of the first end portion to oppose withdraw of the retention clip from the retention aperture when located in the installed position; and wherein the body a reference plane extending through the clip end portions and through the sidewalls of the body, wherein the at least one locking feature extends along the reference plane in a first, compressed state, but extends outwardly from the reference plane in a second, decompressed state to define the ramp, and wherein the reference plane has an arcuate profile establishing opposed concave and convex sides of the body. ### Claim 2 (depends on 1) The stator assembly as recited in claim 1, wherein the retention aperture is an elongated slot having a width that is greater than a width defined between the sidewalls of the body. ### Claim 3 (depends on 2) The stator assembly as recited in claim 2, wherein the retention aperture is dimensioned to cause the at least one locking feature to deflect toward the body when the retention clip is slideably received through the retention aperture. ### Claim 4 (depends on 1) The stator assembly as recited in claim 1, wherein the at least one locking feature is aligned with a respective one of the sidewalls of the body. ### Claim 5 (depends on 1) The stator assembly as recited in claim 1, wherein the at least one locking feature is spaced apart from the sidewalls of the body. ### Claim 6 (depends on 1) The stator assembly as recited in claim 1, wherein the at least one locking feature includes a first locking feature and a second locking feature, and the terminal end of the first locking feature faces toward the terminal end of the second locking feature. ### Claim 7 (depends on 6) The stator assembly as recited in claim 6, wherein each of the first and second locking features decompresses in a direction away from the airfoil body when in the installed position. ### Claim 8 (depends on 6) The stator assembly as recited in claim 6, wherein the retention clip is symmetrical relative to a second reference plane, the second reference plane extends through the sidewalls and is spaced apart from the clip end portions, and the first and second locking features are located on opposite sides of the second reference plane. ### Claim 9 (depends on 6) The stator assembly as recited in claim 6, wherein: the first and second locking features are spaced apart by the body; and the first and second locking features are independently deflectable relative to the body. ### Claim 10 (depends on 9) The stator assembly as recited in claim 9, wherein the first and second locking features are received in respective openings defined in the body in response to respectively deflecting the first and second locking features toward the body. ### Claim 11 (depends on 8) The stator assembly as recited in claim 8, wherein the elongated tab extends outwardly from the concave side in the second, decompressed state. ### Claim 12 A gas turbine engine comprising: a fan section including a plurality of fan blades rotatable about an engine axis; a compressor section in fluid communication with the fan section; a turbine section driving the fan section; and a stator assembly comprising: a first shroud and a second shroud each extending about the engine axis, the first shroud defining an array of first openings, and the second shroud defining an array of second openings; a plurality of airfoils each including an airfoil body extending between first and second end portions, the first end portion situated in a respective one of the array of first openings, and the second end portion situated in a respective one of the array of second openings; and a plurality of retention clips each including an elongated body and at least one locking feature, the body extending between opposed clip end portions and between opposed sidewalls that cooperate to establish a perimeter of the body, the at least one locking feature extending inwardly from a respective one of the clip end portions of the body, and the at least one locking feature of each of the plurality of retention clips compressibly received through a respective one of the first end portions to limit movement of the plurality of airfoils; wherein the body defines a reference plane extending through the clip end portions and through the sidewalls of the body, and wherein the at least one locking feature extends along the reference plane in a first, compressed state, but extends outwardly from the reference plane in a second, decompressed state to define the ramp sloping towards one of the clip end portions, and wherein the reference plane has an arcuate profile establishing opposed concave and convex sides of the body; and wherein the at least one locking feature is an elongated tab having a terminal end that abuts against an external wall of the first end portion in the second, decompressed state to oppose withdraw of a respective one of the plurality of retention clips from a retention aperture of the first end portion when located in the installed position. ### Claim 13 (depends on 12) The gas turbine engine as recited in claim 12, wherein the stator assembly is situated in a bypass flow path aft of the fan section. ### Claim 14 (depends on 12) The gas turbine engine as recited in claim 12, wherein the stator assembly is an inlet guide vane assembly forward of the compressor section. ### Claim 15 (depends on 12) The gas turbine engine as recited in claim 12, wherein the first shroud bounds a radially inner portion of a flow path, and the second shroud bounds a radially outer portion of the flow path. ### Claim 16 A method of assembling a stator assembly for a gas turbine engine comprising: providing a shroud defining a shroud opening; moving an end portion of an airfoil into the shroud opening, the end portion defining a retention aperture; and moving a retention clip relative to the retention aperture, wherein the retention clip includes a body and at least one locking feature extending from the body, the body extends between opposed clip end portions and between opposed sidewalls that cooperate to establish a perimeter of the body, the at least one looking feature is decompressible from the body to define a ramp sloping towards one of the clip end portions, and including moving one of the clip end portions into the retention aperture to cause the at least one locking feature to compress such that the at least one locking feature deflects inward and then through the retention aperture to cause the at least one locking feature to decompress such that the retention clip limits movement of the airfoil relative to the shroud; and wherein the at least one locking feature is an elongated tab having a terminal end that abuts against an external wall of the end portion of the airfoil to oppose withdraw of the retention clip from the retention aperture; and wherein the body defines a reference plane extending through the clip end portions and through the sidewall of the body, wherein the at least one locking feature extends along the reference plane in response to the compressing, but extends outwardly from the reference plane in response to the decompressing to define the ramp, and wherein the reference plane has an arcuate profile establishing opposed concave and convex sides of the body. ### Claim 17 (depends on 16) The method as recited in claim 16, wherein the the retention aperture is an elongated slot dimensioned to contact the ramp. ### Claim 18 (depends on 17) The method as recited in claim 17, wherein the at least one locking feature includes a first locking frame and a second locking feature, the retention clip is symmetrical relative to a second reference plane, the second reference plane extends through the opposed sidewalls and is spaced apart from the clip end portions, and the first and second locking features are located on opposite sides of the second reference plane. ### Claim 19 (depends on 16) The method as recited in claim 16, wherein the at least one locking feature includes a first locking feature and a second locking feature, and the terminal end of the first locking feature faces toward the terminal end of the second locking feature. ### Claim 20 (depends on 19) The method as recited in claim 19, wherein: the first and second locking features are spaced apart by the body of the retention clip; the first and second locking features are independently deflectable relative to the body; the terminal ends of the first and second locking features are dimensioned to abut against opposed sides of the external wall to limit movement of the airfoil relative to the shroud; and the first and second locking features define a first distance between the terminal ends of the first and second locking features in response to the first and second locking features deflecting inward, and the first and second locking features define a second, different distance between the terminal ends of the first and second locking features in response to the first and second locking features decompressing.