# US 11,028,944 B2 · Duct support > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,028,944 B2 - Document ID: US11028944B2 - Status: Granted - Kind: B2 - Application number: 15/994,518 - Filed: 2018-05-31 - Published: 2019-12-05 - Granted: 2021-06-08 - Earliest claimed: 2018-05-31 - Assignees: Textron Innovations Inc. - Applicants: Bell Helicopter Textron Inc. - Inventors: Brent Scannell; Thomas Mast; Jon Damon Bennett; Joshua Allan Edler; Jean Pierre Paradis; Keith C. Pedersen - Web page: https://patentgrep.com/patent/US11028944B2 ## CPC - F16L 3/18: allowing movement in axial direction - B64C 5/00: Stabilising surfaces - F01D 25/00: Component parts, details, or accessories, not provided for in, or of interest apart from, other groups - F01D 25/28: Supporting or mounting arrangements, e.g. for turbine casing - 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) - F16L 3/202: the transverse movement being converted to a rotational movement (F16L3/215 takes precedence) - F16L 3/26: specially adapted for supporting the pipes all along their length, e.g. pipe channels or ducts - B64C 27/04: Helicopters - B64D 33/04: of exhaust outlets or jet pipes - F16L: PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL - B64C: AEROPLANES; HELICOPTERS - 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) - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT ## Abstract One example of a duct support for a rotorcraft includes a stabilizing mechanism configured to transfer a weight of a duct to an airframe of the rotorcraft, where the duct undergoes thermal expansion. The stabilizing mechanism includes a first stabilizing member attached to the duct, a second stabilizing member attached to the rotorcraft, and a coupling mechanism where the coupling mechanism is configured to couple the first stabilizing member to the second stabilizing member and accommodate thermal expansion of the duct by allowing for movement of the first stabilizing member relative to the second stabilizing member. In an example, the duct is an exhaust duct of an engine of the rotorcraft and heat from the engine cause the exhaust duct to undergo the thermal expansion. ## Claims ### Claim 1 A support for a component of a rotorcraft, the support comprising: a stabilizing mechanism configured to transfer a weight of the component to an airframe of the rotorcraft, wherein the component of the rotorcraft undergoes thermal expansion, wherein the stabilizing mechanism includes: a first stabilizing member attached to the component of the rotorcraft; a second stabilizing member attached to the rotorcraft, wherein a portion of the second stabilizing member extends above the airframe of the rotorcraft; and a coupling mechanism located in the portion of the second stabilizing member that extends above the airframe of the rotorcraft, the coupling mechanism including a barrel with a hollow inside portion and a rod that extends through the inside portion of the barrel along a first axis, wherein a portion of the first stabilizing member extends past the coupling mechanism, wherein the coupling mechanism is configured to rotatably couple the first stabilizing member to the second stabilizing member and-allow the first stabilizing member to simultaneously slide back and forth and to rotate relative to the second stabilizing member about the first axis. ### Claim 2 (depends on 1) The support of claim 1, wherein the first stabilizing member is coupled to the rod and can slide back and forth on the rod to accommodate thermal expansion and allow for movement of the first stabilizing member relative to the second stabilizing member. ### Claim 3 (depends on 1) The support of claim 1, wherein the first stabilizing member is secured to the rod and the rod can slide back and forth through the barrel to accommodate thermal expansion and allow for movement of the first stabilizing member relative to the second stabilizing member. ### Claim 4 (depends on 1) The support of claim 1, wherein the first stabilizing member is an integral part of the component. ### Claim 5 (depends on 1) The support of claim 1, wherein the component is an exhaust duct of an engine of the rotorcraft and heat from the engine can cause the exhaust duct to undergo the thermal expansion. ### Claim 6 (depends on 1) The support of claim 1, wherein the first stabilizing member and the portion of the second stabilizing member that extends above the airframe of the rotorcraft extend from the airframe along a second axis, wherein the second axis is substantially perpendicular to the first axis. ### Claim 7 (depends on 1) The support of claim 1, wherein the component is a duct. ### Claim 8 (depends on 7) The support of claim 7, wherein the duct is an exhaust duct. ### Claim 9 A rotorcraft comprising: an airframe configured to support one or more components of the rotorcraft, the one or more components comprising: an aircraft system comprising at least one heat generating element; a duct configured to vent heat from the heat generating element to the environment; a stabilizing mechanism configured to transfer a weight of the duct to the airframe of the rotorcraft, wherein the duct of the rotorcraft undergoes thermal expansion, wherein the stabilizing mechanism includes: a first stabilizing member attached to the duct of the rotorcraft; a second stabilizing member attached to the rotorcraft, wherein a portion of the second stabilizing member extends above the airframe of the rotorcraft; and a coupling mechanism located in the portion of the second stabilizing member that extends above the airframe of the rotorcraft, the coupling mechanism including a barrel with a hollow inside portion and a rod that extends through the inside portion of the barrel along a first axis, wherein a portion of the first stabilizing member extends past the coupling mechanism, wherein the coupling mechanism is configured to rotatably couple the first stabilizing member to the second stabilizing member and allow the first stabilizing member to simultaneously slide back and forth and to rotate relative to the second stabilizing member about the first axis. ### Claim 10 (depends on 9) The rotorcraft of claim 9, wherein the first stabilizing member is coupled to the rod and can slide back and forth on the rod to accommodate thermal expansion and allow for movement of the first stabilizing member relative to the second stabilizing member. ### Claim 11 (depends on 9) The rotorcraft of claim 9, wherein the first stabilizing member is secured to the rod and the rod can slide back and forth through the barrel to accommodate thermal expansion and allowing for movement of the first stabilizing member relative to the second stabilizing member. ### Claim 12 (depends on 9) The rotorcraft of claim 9, wherein the first stabilizing member is an integral part of the duct. ### Claim 13 (depends on 9) The rotorcraft of claim 9, wherein the duct is an exhaust duct. ### Claim 14 (depends on 9) The rotorcraft of claim 9, wherein the heat generating element is an engine, the duct is an exhaust duct of the engine, and heat from the engine can cause the exhaust duct to undergo the thermal expansion.