# US 11,898,682 B2 · System for spacing and fastening tubular structures > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,898,682 B2 - Document ID: US11898682B2 - Status: Granted - Kind: B2 - Application number: 17/451,053 - Filed: 2021-10-15 - Published: 2023-04-20 - Granted: 2024-02-13 - Earliest claimed: 2021-10-15 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Naleen Kumar Verma; Mario Alberto Bolaños Jimenez; Arun Ramachandra; Jeffrey P. Darnell; Michael E. Sandy; José Torre - Web page: https://patentgrep.com/patent/US11898682B2 ## CPC - F16L 3/2235: {each pipe being supported by a common element fastened to the base} - F16L 55/035: in the form of specially adapted hangers or supports - F02C 7/222: {Fuel flow conduits, e.g. manifolds} - F16L 3/10: divided, i.e. with two members engaging the pipe, cable or protective tubing - F16L 57/06: against wear (F16L57/04 takes precedence) - F05D 2220/32: in gas turbines - F05D 2230/60: Assembly methods - F05D 2240/91: on a stationary structure - F05D 2260/96: Preventing, counteracting or reducing vibration or noise - F05D 2260/98: Lubrication - F16L 3/237: for two pipes - F16L 3/24: with special member for attachment to profiled girders - F16L: PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL - 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) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A tube spacing and fastening system for a gas turbine engine includes a plurality of tubular structures, a wear sleeve, a spacer element, and a fastening element. The plurality of tubular structures provides a fluid flow to a component of the gas turbine engine. The wear sleeve is located around each of the plurality of tubular structures. The spacer element receives the plurality of tubular structures. The fastening element extends around the wear sleeves and is configured to secure the plurality of tubular structures to the spacer element. An interference between the fastening element and wear sleeves is configured to allow the fastening element to slide with respect to the wear sleeves and to provide a damping effect under gas turbine engine vibrations and operating conditions. A method of damping vibrations in the plurality of tubular structures includes allowing the fastening element to slide with respect to the wear sleeve. ## Claims ### Claim 1 A tube spacing and fastening system for a gas turbine engine, the tube spacing and fastening system comprising: a plurality of tubular structures configured to provide a fluid flow to a component of the gas turbine engine; a plurality of wear sleeves, each wear sleeve located around a respective one of the plurality of tubular structures; a fastening element configured to extend around the plurality of wear sleeves; a spacer element comprising: a plurality of brackets, each bracket configured to receive a respective wear sleeve of the plurality of wear sleeves; a slot configured to receive the fastening element; and a raised edge adjacent the slot, the raised edge configured to maintain the fastening element within the slot, wherein the fastening element is configured to secure the plurality of tubular structures to the spacer element, wherein an interference between the fastening element and the plurality of wear sleeves is configured to allow the fastening element to slide with respect to the plurality of wear sleeves and to provide a damping effect under gas turbine engine vibrations and operating conditions. ### Claim 2 (depends on 1) The tube spacing and fastening system of claim 1, wherein each wear sleeve of the plurality of wear sleeves is welded or brazed to the respective one of the plurality of tubular structures. ### Claim 3 (depends on 1) The tube spacing and fastening system of claim 1, wherein each wear sleeve of the plurality of wear sleeves is snap fit onto the respective one of the plurality of tubular structures. ### Claim 4 (depends on 1) The tube spacing and fastening system of claim 1, wherein the plurality of wear sleeves controls relative motion of the fastening element and the plurality of tubular structures. ### Claim 5 (depends on 1) The tube spacing and fastening system of claim 1, wherein the fastening element does not form a permanent seal joint with the plurality of wear sleeves. ### Claim 6 (depends on 1) The tube spacing and fastening system of claim 1, wherein an interaction between the fastening element and the plurality of wear sleeves forms a vibration isolation system, the vibration isolation system configured to isolate the plurality of tubular structures from vibrations. ### Claim 7 (depends on 1) The tube spacing and fastening system of claim 1, wherein the fastening element is a shape memory alloy band. ### Claim 8 (depends on 1) The tube spacing and fastening system of claim 1, wherein the plurality of wear sleeves contacts the fastening element, the plurality of tubular structures, and the spacer element. ### Claim 9 (depends on 1) The tube spacing and fastening system of claim 1, wherein each wear sleeve of the plurality of wear sleeves includes a shoulder on each distal end, the shoulder configured to maintain the fastening element at a predetermined longitudinal location on the plurality of tubular structures. ### Claim 10 (depends on 1) The tube spacing and fastening system of claim 1, wherein each wear sleeve of the plurality of wear sleeves is formed of two halves secured around an outer surface of the respective one of the plurality of tubular structures. ### Claim 11 (depends on 10) The tube spacing and fastening system of claim 10, wherein each half of the wear sleeve comprises a protrusion and a recess, and wherein the protrusion on a first half of the wear sleeve is configured to be received in the recess on a second half of the wear sleeve and the protrusion on the second half of the wear sleeve is configured to be received in the recess on the first half of the wear sleeve.