EXHAUST FRAME STRUT WITH COOLING FINS
A system is provided including a turbine exhaust section. The turbine exhaust section includes an exhaust flow path. The turbine exhaust section also includes an outer structure having an outer casing and an outer exhaust wall disposed along the exhaust flow path. An inner structure of the turbine exhaust section includes an inner exhaust wall disposed along the exhaust flow path. A strut extends between the outer structure and the inner structure, and the strut is configured to convey a flow of fluid from the inner structure toward the outer structure. The strut includes a plurality of cooling fins to facilitate heat transfer from the strut to the flow of fluid.
This invention relates generally to gas turbine cooling, and more particularly to exhaust section cooling.
BACKGROUND OF THE INVENTIONA gas turbine engine combusts a mixture of fuel and compressed air to generate hot combustion gases which drive turbine, blades thereby producing energy. The rotation of the turbine blades causes rotation of a shaft supported by bearings. The rotation of the shaft generates a significant amount of heat in the bearings. Additionally, the hot combustion gases exiting through the turbine exhaust section transfer heat w the turbine exhaust section components. Unfortunately, without adequate cooling in the turbine exhaust section, this heat may adversely influence the turbine components.
BRIEF SUMMARY OF THE INVENTIONOne aspect of the disclosed technology relates to a turbine strut that includes a plurality of cooling fins to enhance efficiency of an exhaust section cooling system.
One exemplary but nonlimiting aspect of the disclosed technology relates to a strut for an exhaust section comprising an inner body that is load bearing, the inner body being configured to extend between an outer structure and an inner structure of the exhaust section, the inner body including a main portion and a plurality of cooling fins extending from the main portion; and an outer body configured to extend between the outer structure and the inner structure, of the exhaust section the inner body being disposed in an interior portion of the outer body such that a space is disposed between the main portion of the inner body and the outer body, wherein the space forms an airflow passageway configured to convey a flow of fluid toward the outer structure, and wherein the plurality of cooling fins extend into the airflow passageway and are configured to facilitate heat transfer from the inner body to the flow of fluid.
Another exemplary but nonlimiting aspect of the disclosed technology relates to a system for a gas turbine comprising, a turbine exhaust section, including: an exhaust flow path; an outer structure including an outer casing and an outer exhaust wall disposed along the exhaust flow path; an inner structure including an inner exhaust wall disposed along the exhaust flow path; a strut extending between the outer structure and the inner structure, the strut being configured to convey a flow of fluid from the inner structure toward the outer structure, wherein the strut includes a plurality a cooling fins disposed thereon to facilitate heat transfer from the strut to the flow of fluid.
Other aspects, features, and advantages of this technology will become apparent from the following detailed description when taken in conjunction with the accompanying drawings, which are a part of this disclosure and which illustrate, by way of example, principles of this invention.
The accompanying drawings facilitate an understanding of the various examples of this technology. In such drawings:
Referring to
The illustrated gas turbine engine 12 includes an air intake section 16, a compressor 18, a combustor section 20, a turbine 22, and an exhaust section 24, as shown in
The illustrated combustor section 20 includes a combustor housing 28 disposed concentrically or annularly about the shaft 26 between the compressor 18 and the turbine 22. The compressed air from the compressor 18 enters combustors 30, where the compressed air may mix and combust with fuel within the combustors 30 to drive the turbine 22. From the combustor section 20, the hot combustion gases flow through the turbine 22, driving the compressor 18 via the shaft 26. For example, the combustion gases may apply motive forces to turbine rotor blades within the turbine 22 to rotate the shaft 26. After flowing through the turbine 22, the hot combustion gases may exit the gas turbine engine 12 through the exhaust section 24. As described below, the exhaust section 24 may include a plurality of struts, each having one or more cooling flow paths of the exhaust section cooling system 11.
The exhaust section 24 may include an inner structure (i.e., inner barrel) 3$, at least one strut 40, and an outer structure (i.e., outer barrel) 42, as shown in
Referring to
The outer body 48 also may have greater thermal resistance to the hot combustion gases 31 as compared to the inner body 50. For example, the inner body 50 may have a lower temperature limit than the outer body 48. In some embodiments, the inner body 50 may have a temperature limit lower than the temperature of the hot combustion gases 31, while the outer body 48 may have a temperature limit substantially above the temperature of the hot combustion gases. Thus, the outer body 48 thermally protects the inner body 50, such that the inner body 50 is able to effectively bear the mechanical load between the inner and outer structures 38 and 42 of the exhaust section 24.
Referring to
As shown in
Referring to
As efficiency of the cooling, airflow 93 is enhanced, the amount of airflow required to achieve a certain led of Ana cooling is reduced. Energy required to provide the cooling airflow directly impacts turbine efficiency. Thus, the cooling fins enable the power consumption of the airflow source (e.g., blower) to be reduced, thereby increasing turbine efficiency. It is possible that the need for a blower can be eliminated.
As shown in
The cooling fins 55 may extend over the entire radial length of the main portion 53, as shown in
Referring to
Referring to
Turning to
In another example, an inner body 250 includes a main portion 253 and cooling fins 255 protruding from the main portion, as shown in
While the invention has been described in connection with what is presently considered to be the most practical and preferred examples, it is to be understood that the invention is not to be limited to the disclosed examples, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.
Claims
1. A strut for an exhaust section, comprising:
- an inner body that is load bearing, the inner body being configured to extend between an outer structure and an inner structure of the exhaust section, the inner body including a main portion and a plurality of cooling fins extending from the main portion; and
- an outer body configured to extend between the outer structure and the inner structure of the exhaust section, the inner body being disposed in an interior portion of the outer body such that a space is disposed between the main portion of the inner body and the outer body,
- wherein the space forms an airflow passageway configured to convey a flow of fluid toward the outer structure, and
- wherein the plurality of cooling fins extend into the airflow passageway and are configured to facilitate heat transfer from the inner body to the flow of fluid.
2. The strut according to claim 1, wherein the outer both has an inner surface which faces the inner body, and the inner surface has a coating with low thermal conductivity.
3. The strut according to claim 1, further comprising an insulating material disposed between the outer body and the main portion of the inner body.
4. The strut according to claim 3, wherein the insulating material contacts tip portions of the plurality of cooling fins such that the flow of fluid can pass along channels formed between adjacent cooling fins.
5. The strut according to claim 3, wherein a first portion of the plurality of cooling, fins protrude further from the main portion of the inner body than a second portion of the plurality of cooling fins.
6. The strut according to claim 5, wherein the insulating material contacts tip portions of the first portion of the plurality of cooling fins such that the flow of fluid can pass between the insulating material and the second portion of the plurality of cooling fins.
7. The strut according to claim 1, wherein each cooling fin of the plurality of cooling fins forms an elongate member extending in an axial direction of the exhaust section.
8. The strut according to claim 1, wherein each cooling fin of the plurality of cooling fins loans an elongate member extending in a radial direction of the exhaust section.
9. The strut according to claim 8, wherein a distance that the plurality of cooling fins extend from the main portion of the inner body varies along the radial direction.
10. The strut according to claim 1, wherein a distance between adjacent fins of the plurality of cooling fins varies over the main portion of the inner body.
11. A system for a gas turbine, comprising:
- a turbine exhaust section, including: an exhaust flow path; an outer structure including an outer casing and an outer exhaust wall disposed along the exhaust flow path; an inner structure including an inner exhaust wall disposed along the exhaust flow path; a strut extending between the outer structure and the inner structure, the strut being configured to convey a flow of fluid from the inner structure toward the outer structure, wherein the strut includes a plurality of cooling fins disposed thereon to facilitate heat transfer from the strut to the flow of fluid.
12. The system according to claim 11, wherein the strut includes an inner body that is load bearing and an outer body that is not load bearing.
13. The system according to claim 12, wherein the inner body includes a main portion, and the plurality of cooling fins extend from the main portion.
14. The system according to claim 13, wherein the inner body is disposed in an interior portion of the outer body such that a space is disposed between the main portion of the inner body and the outer body.
15. The system according to claim 14, wherein the space forms an airflow passageway configured to convey the flow of fluid toward the outer structure.
16. The system according to claim 15, wherein the plurality of cooling fins extend into the airflow passageway.
17. The system according to claim 13, further comprising an insulating material disposed between the outer body and die main portion of the inner body.
18. The system according to claim 12, wherein the outer body has an inner surface which faces the inner body, and the inner surface has a coating with low thermal conductivity.
19. The system according to claim 11, wherein each cooling fin of the plurality of cooling fins forms an elongate member extending in an axial direction or a radial direction of the turbine exhaust section.
20. A gas turbine, comprising:
- a compressor;
- a combustor section;
- a turbine section; and
- the system of claim 11.
Type: Application
Filed: Sep 9, 2015
Publication Date: Mar 9, 2017
Inventors: Debabrata MUKHOPADHYAY (Bangalore), Rohit PRUTHI (Bangalore)
Application Number: 14/849,112