# US 2014/0190180 A1 · Fairing of a gas turbine structure > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2014/0190180 A1 - Document ID: US20140190180A1 - Status: Published application - Kind: A1 - Application number: 14/117,255 - Filed: 2011-05-16 - Published: 2014-07-10 - Earliest claimed: 2011-05-16 - Assignees: GKN Aerospace Sweden AB - Inventors: Harald Söderlund; Andreas Borg - Web page: https://patentgrep.com/patent/US20140190180A1 ## CPC - F02C 7/20: Mounting or supporting of plant; Accommodating heat expansion or creep - F01D 25/162: {Bearing supports} - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F05D 2230/642: using maintaining alignment while permitting differential dilatation - 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) - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A gas turbine structure includes a first housing and a second housing, one of the first and second housings being located around the other of the first and second housings such that a core flow passage is obtained between the first and second housings. The gas turbine structure further includes an elongate structural member extending in a structural member direction from the first housing to the second housing and the gas turbine structure further includes a fairing circumferentially enclosing at least a portion of the structural member. ## Claims ### Claim 1 A gas turbine structure comprising a first housing and a second housing, one of the first and second housings being located around the other of the first and second housings such that a core flow passage is obtained between the first and second housings, an elongate structural member extending in a structural member direction from the first housing to the second housing, a fairing circumferentially enclosing at least a portion of the structural member, the fairing extending in a fairing direction substantially parallel to the structural member direction, the fairing comprising a fairing attachment portion attached to the first housing such that a displacement of the fairing attachment portion in relation to the first housing is prevented at least in the fairing direction, the fairing further comprising a fairing end portion located at the other end of the fairing in the fairing extension direction as compared to the fairing attachment portion, wherein the fairing end portion is allowed to be displaced, in at least the fairing direction, in relation to the second housing. ### Claim 2 (depends on 1) The gas turbine structure according to claim 1, wherein the structural member comprises a first stand-up and an intermediate member, the first stand-up being attached to the first housing and the intermediate member being attached to the first stand-up by means of a first stand-up joint, at least a portion of the fairing extending past the first stand-up joint in the structural member direction. ### Claim 3 (depends on 1) The gas turbine structure according to claim 1, wherein the structural member has a structural member length in the structural member direction from the first housing to the second housing and the fairing having a fairing length from the first housing in the fairing direction, the fairing length being smaller than the structural member length. ### Claim 4 (depends on 3) The gas turbine structure according to claim 3, wherein the fairing length is less than 90%, preferably less than 50%, more preferred less than 30%, of the structural member length. ### Claim 5 (depends on 1) The gas turbine structure according to claim 1, wherein the structural member comprises a leading structural member portion and a trailing structural member portion, the trailing structural member portion being arranged to be located downstream of the leading structural member portion when the gas turbine engine is operated to produce a core fluid flow through the gas turbine structure, the fairing comprising a first fairing portion and a second fairing portion, the first fairing portion covering the leading structural member portion and the second fairing portion covering the trailing structural member portion, the first fairing portion and the second fairing portion contacting one another in a contacting area comprising a first axial split line and a second axial split line. ### Claim 6 (depends on 5) The gas turbine structure according to claim 5, wherein the fairing comprises a leading edge and a trailing edge, the fairing extends from the leading edge to the trailing edge along a mean camber line, the fairing further comprising a fairing thickness measured in a direction perpendicular to the mean camber line, the fairing further having a maximum thickness between the leading edge and the trailing edge, the fairing further having a suction side and a pressure side, the first axial split line being located on the suction side between the maximum thickness and the trailing edge when measured along the mean camber line. ### Claim 7 (depends on 6) The gas turbine structure according to claim 6, wherein the second axial split line is located on the pressure side, the second axial split line being located closer to the leading edge, when measured along the mean camber line, than the first axial split line. ### Claim 8 (depends on 5) The gas turbine structure according to claim 5, wherein the first fairing portion overlaps the second fairing portion in the contacting area. ### Claim 9 (depends on 1) The gas turbine structure according to claim 1, wherein the structural member has an structural member outer surface and the fairing has an inner fairing surface, the gas turbine structure comprising a fairing gap being the distance in a direction normal to the structural member outer surface from the structural member outer surface to the fairing inner surface, the gas turbine structure comprising a fairing closure, the fairing closure being configured such that the fairing gap at the fairing closure is smaller than the average fairing gap at the remaining portion of the fairing. ### Claim 10 (depends on 9) The gas turbine structure according to claim 9, wherein the fairing gap (ΔP) at the fairing closure is less than 50%, preferably less than 30%, of the average fairing gap (ΔP) at the remaining portion of the fairing. ### Claim 11 (depends on 9) The gas turbine structure according to claim 9, wherein the fairing closure comprises a flanged portion of the fairing. ### Claim 12 (depends on 1) The gas turbine structure according to claim 1, wherein the gas turbine structure comprises an additional fairing circumferentially enclosing at least a portion of the circumference of the structural member, the additional fairing extending in an additional fairing direction substantially parallel to the structural member direction, the additional fairing comprising an additional fairing attachment portion attached to the second housing such that a displacement of the additional fairing attachment portion in relation to the second housing is prevented at least in the additional fairing direction, the additional fairing further comprising and an additional fairing end portion located at the other end of the additional fairing in the additional fairing extension direction as compared to the additional fairing attachment portion, the additional fairing end portion being allowed to be displaced, in at least the additional fairing direction, in relation to the first housing. ### Claim 13 (depends on 1) The gas turbine structure according to claim 1, wherein the gas turbine structure is a rear gas turbine structure. ### Claim 14 (depends on 1) A gas turbine engine comprising a gas turbine structure according to claim 1. ### Claim 15 (depends on 14) An aeroplane comprising a gas turbine engine according to claim 14. ### Claim at position 16 16-30. (canceled)