System for spacing and fastening tubular structures
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.
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.
2. 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.
3. 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.
4. 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.
5. 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.
6. 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.
7. The tube spacing and fastening system of claim 1 , wherein the fastening element is a shape memory alloy band.
8. 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.
9. 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.
10. 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.
11. 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.