Thermal isolating service tubes and assemblies thereof for gas turbine engines

Patent metadata

Field	Value
Publication number	US-9644495-B2
Application number	US-201313971671-A
Country	US
Kind code	B2
Filing date	Aug 20, 2013
Priority date	Aug 20, 2013
Publication date	May 9, 2017
Grant date	May 9, 2017

Abstract

Thermal isolating service tubes and assemblies thereof for gas turbine engines are provided. The thermal isolating service tube comprises an inner tubular member defining a fluid passage and at least one outer tubular member disposed about the inner tubular member. A spacing volume is defined between at least the inner tubular member and an adjacent outer tubular member. The thermal isolating service tube comprises a unitary structure and has at least one portion with a curved configuration, a non-circular cross-sectional shape, or both.

First claim

What is claimed is:

1. A service tube assembly for a gas turbine engine, comprising:
an external structure associated with the gas turbine engine having a non-cylindrical opening therethrough;
a thermal isolating service tube including:
an inner tubular member defining a fluid passage through which a first fluid flows;
at least one outer tubular member disposed about the inner tubular member to define a spacing volume therebetween, the spacing volume defining a second fluid passage for receiving a second fluid, and an outermost outer tubular member of the at least one outer tubular member has an end portion terminating in a mounting flange, the mounting flange is substantially thermally isolated from the inner tubular member by at least one wall that extends from the end portion to define a second spacing volume between the mounting flange and the outermost outer tubular member, the at least one wall coupled to the end portion at a first end and coupled to the mounting flange at a second end; and
at least one spacer defined from the inner tubular member that extends radially toward the at least one outer tubular member in the spacing volume such that a gap is defined between the spacer and an interior wall of the at least one outer tubular member in the spacing volume,

wherein the thermal isolating service tube comprises a unitary structure and has at least one portion with a curved configuration, a non-circular cross-sectional shape, or both.

2. The service tube assembly of claim 1 , wherein the inner tubular member has a cross-sectional shape that is different from a cross-sectional shape of the at least one outer tubular member.

3. The service tube assembly of claim 2 , wherein at least one of the inner tubular member or the at least one outer tubular member comprises a non-cylindrical tubular member.

4. The service tube assembly of claim 1 , wherein the unitary structure comprises a non-cylindrical tubular structure.

5. The service tube assembly of claim 1 , wherein the unitary structure has the at least one portion with the non-circular cross-sectional shape and an adjacent portion with a circular cross-sectional shape.

6. The service tube assembly of claim 1 , wherein the unitary structure has the at least one portion with the non-circular cross-sectional shape and an adjacent portion with a different non-circular cross-sectional shape.

7. The service tube assembly of claim 1 , wherein the at least one portion of the thermal isolating service tube is configured and dimensioned to pass through the non-cylindrical opening in the external structure.

8. The service tube assembly of claim 7 , wherein the non-cylindrical opening in the external structure has substantially the same cross-sectional shape as a cross-sectional shape of the at least one portion of the thermal isolating service tube.

9. The service tube assembly of claim 1 , wherein the second fluid is a cooling fluid for cooling the inner tubular member, and the first fluid is oil.

10. A service tube assembly for a gas turbine engine, comprising:
an external structure associated with the gas turbine engine having a non-cylindrical opening therethrough; and
a unitary thermal isolating service tube comprising an inner tubular member defining a fluid passage through which a first fluid flows and at least one outer tubular member disposed about the inner tubular member to define a spacing volume therebetween, the spacing volume defining a second fluid passage for receiving a second fluid, with at least one spacer defined from the inner tubular member that extends radially toward the at least one outer tubular member in the spacing volume such that a gap is defined between the spacer and an interior wall of the at least one outer tubular member in the spacing volume and an outermost outer tubular member of the at least one outer tubular member has an end portion terminating in a mounting flange, the mounting flange is substantially thermally isolated from the inner tubular member by at least one wall that extends from the end portion to define a second spacing volume between the mounting flange and the outermost outer tubular member, the at least one wall coupled to the end portion at a first end and coupled to the mounting flange at a second end,
wherein at least one portion of the unitary thermal isolating service tube is configured with a non-circular cross-sectional shape and dimensioned to pass through the non-cylindrical opening.

11. The service tube assembly of claim 10 , wherein the non-cylindrical opening in the external structure has substantially the same cross-sectional shape as a cross-sectional shape of the at least one portion of the unitary thermal isolating service tube.

12. The service tube assembly of claim 11 , wherein the at least one portion of the unitary thermal isolating service tube has the non-circular cross-sectional shape, and an adjacent portion of the unitary thermal isolating service tube has a circular cross-sectional shape.

13. The gas turbine engine of claim 10 , wherein the fluid is oil or air, and the second fluid is a cooling fluid for cooling the inner tubular member.

14. A gas turbine engine comprising:
a rotor bearing in a bearing sump of the gas turbine engine, and
an oil system for lubricating and cooling the rotor bearing with oil when the gas turbine engine is operating, wherein the oil system is coupled to a plurality of service tubes and at least one service tube of the plurality of service tubes comprises a thermal isolating service tube, the thermal isolating service tube comprising:
an inner tubular member defining a fluid passage in communication with the oil system through which a fluid flows; and
at least one outer tubular member disposed about the inner tubular member and defining a spacing volume between at least the inner tubular member and the at least one outer tubular member, the spacing volume defining a second fluid passage for receiving a second fluid, with at least one spacer defined from the inner tubular member that extends radially toward the at least one outer tubular member in the spacing volume such that a gap is defined between the spacer and an interior wall of the at least one outer tubular member in the spacing volume and an outermost outer tubular member of the at least one outer tubular member has an end portion terminating in a mounting flange, the mounting flange is substantially thermally isolated from the inner tubular member by at least one wall that extends from the end portion to define a second spacing volume between the mounting flange and the outermost outer tubular member, the at least one wall coupled to the end portion at a first end and coupled to the mounting flange at a second end, and
wherein the thermal isolating service tube comprises a unitary structure and has at least one portion with a curved configuration, a non-circular cross-sectional shape, or both.

15. The gas turbine engine of claim 14 , wherein the at least one portion of the thermal isolating service tube is configured and dimensioned to pass through a non-cylindrical opening in an external structure within the gas turbine engine.

16. The gas turbine engine of claim 15 , wherein the external structure comprises a stationary structural frame, a fairing, or a diffuser housing.

17. The gas turbine engine of claim 14 , wherein the non-cylindrical opening in the external structure has substantially the same cross-sectional shape as a cross-sectional shape of the at least one portion of the thermal isolating service tube.

18. The gas turbine engine o

Assignees

• Honeywell Int Inc

Inventors

• Zurmehly Ed
• Frost Cristopher
• O'Brien Michael
• Godfrey Donald G

Classifications

• F01D25/18

  Lubricating arrangements (of machines or engines in general F01M) · CPC title

• F01D25/145

  Thermally insulated casings · CPC title

• F01D25/26

  Double casings; Measures against temperature strain in casings · CPC title

• F01D25/125 Primary

  of bearings · CPC title

• F01D9/065

  Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26) · CPC title