# US 11,028,782 B2 · Pressure relief arrangement 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 11,028,782 B2 - Document ID: US11028782B2 - Status: Granted - Kind: B2 - Application number: 16/124,559 - Filed: 2018-09-07 - Published: 2019-04-18 - Granted: 2021-06-08 - Earliest claimed: 2017-10-12 - Assignees: ROLLS-ROYCE plc - Applicants: ROLLS-ROYCE plc - Inventors: Simon M. Ruston; Rong Yang; Matthew Fox; Aniket Anand Kulkarni - Web page: https://patentgrep.com/patent/US11028782B2 ## CPC - F02C 7/00: Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants (controlling F02C9/00) - F02C 9/18: by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} - B64D 29/00: Power-plant nacelles, fairings or cowlings - B64D 29/08: Inspection panels for power plants - F01D 21/14: responsive to other specific conditions - F01D 25/24: Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) - F02K 3/06: with front fan - F02K 3/075: controlling flow ratio between flows - F05D 2260/30: Retaining components in desired mutual position - 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) - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - 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 ## Abstract A pressure relief arrangement for a gas turbine engine comprises a hinged door and a mount. A plastically deformable member is provided between and coupled to the hinged door and the mount. The deformable member is configured to deform between a non-deformed state when the door is in a closed position and an elongated deformed state when the door is in an open position. ## Claims ### Claim 1 A gas turbine engine comprising a pressure relief arrangement pressure relief arrangement including a hinged door; a mount; and a plastically deformable member provided between and coupled to the hinged door and the mount, the deformable member being configured to deform between a non-deformed state when the door is in a closed position and an elongated deformed state when the door is in an open position, wherein the plastically deformable member is coupled to the hinged door via an articulated link. ### Claim 2 (depends on 1) The gas turbine engine according to claim 1, wherein the articulated link is pivotally connected to the door and to the plastically deformable member, so that the articulated link can pivot between a first position when the door is in the closed position and a second position when the door is in the open position. ### Claim 3 A gas turbine engine comprising a pressure relief arrangement pressure relief arrangement including a hinged door; a mount; and a plastically deformable member provided between and coupled to the hinged door and the mount, the deformable member being configured to deform between a non-deformed state when the door is in a closed position and an elongated deformed state when the door is in an open position, wherein the plastically deformable member is made from a plurality of stacked elements, each stacked element extending fully between the opposite ends of the plastically deformable member. ### Claim 4 (depends on 3) The gas turbine engine according to claim 3, wherein the stacked elements are identical in shape and size, and optionally material. ### Claim 5 (depends on 3) The gas turbine engine according to claim 3, wherein the stacked elements are cut from sheet or plate. ### Claim 6 A gas turbine engine comprising a pressure relief arrangement pressure relief arrangement including a hinged door; a mount; and a plastically deformable member provided between and coupled to the hinged door and the mount, wherein the plastically deformable member comprises one or more bends that deviate from a linear path between opposite ends of the plastically deformable member, the plastically deformable member being configured to deform between a non-deformed state in which the plastically deformable member has a first length measured between the opposite ends of the plastically deformable member in a direction of the linear path when the door is in a closed position and an elongated deformed state in which the one or more bends straighten out and cause the plastically deformable member to plastically deformed and have a second length measured between the opposite ends of the plastically deformable member in the direction of the linear path when the door is in an open position, the second length being greater than the first length. ### Claim 7 (depends on 6) The gas turbine engine according to claim 6, wherein each of the one or more bends of the plastically deformable member curve through 180°. ### Claim 8 (depends on 6) The gas turbine engine according to claim 6, wherein the radius of each bend of the one or more bends is at least five times the width of the plastically deformable member measured in a plane parallel to the plane in which the radius of curvature lies. ### Claim 9 (depends on 6) The gas turbine engine according to claim 6, wherein the one or more bends are asymmetric about a line that extends between the opposite ends of the plastically deformable member. ### Claim 10 (depends on 6) The gas turbine engine according to claim 6, wherein the one or more bends are symmetric about a line that extends between the opposite ends of the plastically deformable member. ### Claim 11 (depends on 6) The gas turbine engine according to claim 6, wherein the plastically deformable member is made from a metal. ### Claim 12 (depends on 6) The gas turbine engine according to claim 6, comprising an engine core, and a casing member surrounding the engine core, and wherein the mount is provided radially internally of the core casing member and the door being arranged to pivot outwardly away from the core. ### Claim 13 (depends on 6) The gas turbine engine according to claim 6, wherein each of the one or more bends is U-shaped. ### Claim 14 (depends on 6) The gas turbine engine according to claim 6, wherein the plastically deformable member is pivotably coupled with the hinged door and pivotably coupled with the mount. ### Claim 15 (depends on 6) The gas turbine engine according to claim 6, wherein the one or more bends comprises alternating convex and concave curves. ### Claim 16 (depends on 6) The gas turbine engine according to claim 6, wherein the plastically deformable member is made from a plurality of stacked elements, each stacked element extending fully between the opposite ends of the plastically deformable member.