# US 10,480,386 B2 · Exhaust manifold for combining system exhaust plume > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,480,386 B2 - Document ID: US10480386B2 - Status: Granted - Kind: B2 - Application number: 15/713,207 - Filed: 2017-09-22 - Published: 2019-03-28 - Granted: 2019-11-19 - Earliest claimed: 2017-09-22 - Assignees: Bell Helicopter Textron Inc. - Applicants: Bell Helicopter Textron Inc. - Inventors: Keith C. Pedersen; Brent Scannell; Nam Dai Tran; Thomas Mast - Web page: https://patentgrep.com/patent/US10480386B2 ## CPC - F01N 13/10: of exhaust manifolds {(with cooling jacket F01N3/046)} - B64C 27/00: Rotorcraft; Rotors peculiar thereto - B64D 33/08: of power plant cooling systems - F01P 1/06: Arrangements for cooling other engine or machine parts - F01P 11/10: Guiding or ducting cooling-air, to, or from, liquid-to-air heat exchangers - F01N: GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL-COMBUSTION ENGINES (arrangements in connection with gas exhaust of propulsion units in vehicles B60K13/00; combustion-air intake silencers specially adapted for, or arranged on, internal-combustion engines F02M35/00; protecting against, or damping, noise in general G10K11/16) - B64C: AEROPLANES; HELICOPTERS - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - F01P: COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES (arrangements in connection with cooling of propulsion units in vehicles B60K11/00; heat-transfer, heat-exchange or heat-storage materials C09K5/00; {cooling of gas-turbine engines F02C7/12}; heat exchange in general, radiators F28) ## Abstract Disclosed herein is an aircraft that includes an exhaust manifold for combining one or more system exhaust paths located upstream of equipment inlets and directing the exhausts upwards towards the rotor linkages such that the exhaust is expelled and diffused forward of the equipment inlets. According to one aspect of the present disclosure, the exhaust manifold includes a structure for supporting a transmission cowling at the top of the aircraft and/or on the sides of the aircraft. For example, the exhaust manifold may include a platform that contains the exhaust ducts and may include a frame extending from the platform that follows the contours of the cowling, such that the cowling lays along the support frame for additional mechanical support. ## Claims ### Claim 1 An exhaust manifold for an aircraft comprising: a plurality of exhaust ducts in gaseous communication with one or more exhaust systems, wherein the exhaust ducts receive exhaust from the one or more exhaust systems; and a platform comprising the plurality of exhaust ducts, wherein the platform is located upstream of an equipment inlet, and wherein the plurality of exhaust ducts are configured to direct exhaust at a rotor linkage for the exhaust to dissipate away from one or more rotors attached to the rotor linkage. ### Claim 2 (depends on 1) The exhaust manifold of claim 1, wherein the one or more exhaust systems include one or more of a transmission, an oil cooling, a generator, and an environmental control system. ### Claim 3 (depends on 1) The exhaust manifold of claim 1, further comprising: a cowl, wherein the platform is attached to the cowl; and a cowl support structure, wherein the cowl support structure supports the cowl to which the platform is attached. ### Claim 4 (depends on 3) The exhaust manifold of claim 3, wherein the cowl support structure matches a contour of the cowl. ### Claim 5 (depends on 3) The exhaust manifold of claim 3, wherein the cowl support structure matches a portion of a contour of the cowl. ### Claim 6 An apparatus, comprising: a plurality of exhaust ducts in gaseous communication with one or more exhaust systems, wherein the exhaust ducts receive exhaust from the one or more exhaust systems; and a platform comprising the plurality of exhaust ducts, wherein the platform is located upstream of an equipment inlet, and wherein the plurality of exhaust ducts direct exhaust at a rotor linkage for the exhaust to dissipate away from one or more rotors attached to the rotor linkage. ### Claim 7 (depends on 6) The apparatus of claim 6, wherein the one or more exhaust systems include one or more of a transmission, an oil cooling, a generator, and an environmental control system. ### Claim 8 (depends on 6) The apparatus of claim 6, further comprising: a cowl, wherein the platform is attached to the cowl; and a cowl support structure, wherein the cowl support structure supports the cowl to which the platform is attached. ### Claim 9 (depends on 8) The apparatus of claim 8, wherein the cowl support structure matches a contour of the cowl. ### Claim 10 (depends on 8) The apparatus of claim 8, wherein the cowl support structure matches a portion of a contour of the cowl. ### Claim 11 A rotorcraft, comprising: an engine; an engine inlet; a rotor linkage; and an exhaust manifold comprising: a plurality of exhaust ducts in gaseous communication with one or more exhaust systems, wherein the exhaust ducts receive exhaust from the one or more exhaust systems; and a platform comprising the plurality of exhaust ducts, wherein the platform is located upstream of the engine inlet, and wherein the plurality of exhaust ducts are configured to direct exhaust at the rotor linkage for the exhaust to dissipate away from one or more rotors attached to the rotor linkage. ### Claim 12 (depends on 11) The rotorcraft of claim 11, wherein the one or more exhaust systems include one or more of a transmission, an oil cooling, a generator, and an environmental control system. ### Claim 13 (depends on 11) The rotorcraft of claim 11, further comprising: a cowl, wherein the platform is attached to the cowl; and a cowl support structure, wherein the cowl support structure supports the cowl to which the platform is attached. ### Claim 14 (depends on 13) The rotorcraft of claim 13, wherein the cowl support structure matches a contour of the cowl. ### Claim 15 (depends on 13) The rotorcraft of claim 13, wherein the cowl support structure matches a portion of a contour of the cowl.