# US 10,246,198 B2 · Alignment system for exhaust installation > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,246,198 B2 - Document ID: US10246198B2 - Status: Granted - Kind: B2 - Application number: 15/026,555 - Filed: 2014-08-29 - Published: 2016-08-25 - Granted: 2019-04-02 - Earliest claimed: 2013-10-01 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Brett Colin Bonner; Eric Andrew Nager - Web page: https://patentgrep.com/patent/US10246198B2 ## CPC - B64D 33/04: of exhaust outlets or jet pipes - B64D 41/00: Power installations for auxiliary purposes - F01D 25/28: Supporting or mounting arrangements, e.g. for turbine casing - F01D 25/30: Exhaust heads, chambers, or the like - F02C 7/20: Mounting or supporting of plant; Accommodating heat expansion or creep - F02K 1/04: Mounting of an exhaust cone in the jet pipe - B64D 2041/002: {Mounting arrangements for auxiliary power units (APU's)} - F05D 2220/50: for auxiliary power units (APU's) - F05D 2230/60: Assembly methods - F05D 2230/644: for adjusting the position or the alignment, e.g. wedges or eccenters - F05D 2250/241: spherical - F05D 2250/711: convex - F05D 2250/712: concave - F05D 2260/30: Retaining components in desired mutual position - 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) - 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 ## Abstract An exhaust system for an aircraft includes an exhaust duct configured to be inserted within a plurality of leaf springs of an aircraft. The exhaust duct is configured to be in fluid communication with the auxiliary power unit for conveying exhaust from the auxiliary power unit to an exhaust exit, the exhaust duct including at least one exhaust bracket for movably mounting the exhaust duct to an airframe. An alignment system is configured to be operatively connected to the exhaust duct. ## Claims ### Claim 1 An exhaust system for an aircraft comprising: an exhaust duct configured to be in fluid communication with an auxiliary power unit for conveying exhaust from the auxiliary power unit to an exhaust exit, the exhaust duct including at least two exhaust brackets for movably mounting the exhaust duct to an airframe; and an alignment system configured to be operatively connected to the exhaust duct, wherein the alignment system includes, disposed between each exhaust bracket and the aircraft frame, at least one tapered shim adjacent the exhaust duct for accommodating a gap between the at least one exhaust bracket and the airframe. ### Claim 2 (depends on 1) The exhaust system as recited in claim 1, wherein the alignment system includes at least one convex washer disposed between each exhaust bracket and the associated tapered shim. ### Claim 3 (depends on 1) The exhaust system as recited in claim 1, wherein the alignment system includes at least one concave washer disposed between each exhaust bracket and the associated tapered shim. ### Claim 4 (depends on 1) The exhaust system as recited in claim 1, wherein the alignment system includes at least one convex washer disposed on a side of each exhaust bracket opposite the associated tapered shim. ### Claim 5 (depends on 1) The exhaust system as recited in claim 1, wherein the alignment system includes at least one concave washer disposed on a side of each exhaust bracket opposite the tapered shim. ### Claim 6 (depends on 1) The exhaust system as recited in claim 1, wherein the alignment system includes at least one convex washer and at least one concave washer engaged together and disposed between each exhaust bracket and the tapered shim. ### Claim 7 (depends on 1) The exhaust system as recited in claim 1, wherein the alignment system includes at least one convex washer and at least one concave washer engaged together and disposed on a side of each exhaust bracket opposite the tapered shim. ### Claim 8 A method for aligning an aircraft exhaust system, the steps comprising: inserting an exhaust duct into a plurality of leaf springs of a tail cone; identifying a gap between each of two exhaust brackets and an aircraft frame; operatively connecting an alignment system to the exhaust duct to secure each exhaust bracket to the aircraft frame across the each gap; and wherein the step of connecting includes inserting a tapered shim into each gap. ### Claim 9 (depends on 8) The method as recited in claim 8, wherein the step on inserting the exhaust duct includes attaching the exhaust duct at a first attachment point. ### Claim 10 (depends on 9) The method as recited in claim 9, wherein the step of connecting includes disposing at least one convex and at least one concave washer between each exhaust bracket and the tapered shim. ### Claim 11 (depends on 9) The method as recited in claim 9, wherein the step of connecting includes disposing at least one convex and at least one concave washer on a side of each exhaust bracket opposite the tapered shim. ### Claim 12 (depends on 9) The method as recited in claim 9, further comprising bolting the tapered shim to the aircraft frame.