Gas turbine engine having a casing provided with cooling fins

Patent metadata

Field	Value
Publication number	US-2018112552-A1
Application number	US-201615568919-A
Country	US
Kind code	A1
Filing date	Apr 22, 2016
Priority date	Apr 24, 2015
Publication date	Apr 26, 2018
Grant date	—

Abstract

The gas turbine engine ( 3 ) comprises a compressor section ( 9 ) configured for compressing combustion air, a combustor section ( 15 ) and a turbine section ( 21 ). The turbine section ( 21 ) comprises a turbine rotor ( 41 ) with a bladed wheel ( 43 ) rotating around a turbine rotation axis (A-A), an exhaust gas diffuser ( 65 ), and a casing ( 52 ) having an inner surface and an outer surface. The casing ( 52 ) further comprises a plurality of cooling fins ( 75 ) located on the outer surface thereof.

First claim

1 . A gas turbine engine ( 3 ) comprising:
a compressor section ( 9 ) configured for compressing combustion air; a combustor section ( 15 ) configured for receiving a flow of compressed air ( 11 ) from the compressor section ( 9 ) and a fuel ( 17 ) and for burning a fuel-air mixture generating a flow of hot pressurized combustion gases ( 19 ); a turbine section ( 21 ) configured for receiving the hot pressurized combustion gases ( 19 ) and expanding the combustion gases to generate mechanical power; the turbine section ( 21 ) comprising a turbine rotor ( 41 ) with at least one bladed wheel ( 43 ) rotating around a turbine rotation axis (A-A), an exhaust gas diffuser ( 65 ), and a casing ( 52 ) having an inner surface and an outer surface; wherein the casing ( 52 ) comprises a plurality of cooling fins ( 75 ) located on the outer surface thereof.

2 . The gas turbine engine of claim 1 , wherein the cooling fins ( 75 ) have an annular shape, surrounding the rotation axis (A-A) of the turbine rotor ( 41 ).

3 . The gas turbine engine of claim 1 or 2 , wherein the cooling fins ( 75 ) are arranged circularly around the at least one bladed wheel ( 43 ).

4 . The gas turbine engine of claim 1 or 2 or 3 , wherein the turbine section ( 9 ) comprises at least one shroud ( 59 ) encircling the at least one bladed wheel ( 43 ) and connected to the casing ( 52 ), and wherein the cooling fins ( 75 ) are arranged around the shroud ( 59 ).

5 . The gas turbine engine of one or more of the preceding claims, wherein the casing ( 52 ) comprises a turbine casing portion ( 52 A) and a diffuser casing portion ( 52 B) connected to one another, and wherein the cooling fins ( 75 ) are arranged at or near a connection between the turbine casing portion ( 52 A) and the diffuser casing portion ( 52 B).

6 . The gas turbine engine of one or more of claims 1 to 4 , wherein the casing ( 52 ) comprises a turbine casing portion ( 52 A) and a diffuser casing portion ( 52 B) connected to one another at a connection region, and wherein the cooling fins ( 75 ) are formed on the diffuser casing portion ( 52 B) at or near the connection region.

7 . The gas turbine engine of one or more of claims 1 to 4 , wherein the casing ( 52 ) comprises a turbine casing portion ( 52 A) and a diffuser casing portion ( 52 B), connected to one another, wherein the turbine casing portion ( 52 A) has a first connection flange ( 67 ) and the diffuser casing portion ( 52 B) has a second connection flange ( 69 ), and wherein the diffuser casing portion ( 52 B) and the turbine casing portion ( 52 A) are connected to one another at the first connection flange and second connection flange.

8 . The gas turbine engine of claim 7 , wherein the cooling fins ( 75 ) are formed around the second connection flange ( 69 ).

9 . The gas turbine engine of claims 4 and 7 or 4 and 8 , wherein an intermediate annular casing component ( 73 ) is arranged between the first connection flange ( 67 ) and the second connection flange ( 69 ), the shroud ( 59 ) being constrained to and supported by the intermediate annular casing component ( 73 ).

10 . The gas turbine engine of claim 9 , wherein the intermediate annular casing component ( 73 ) extends substantially coaxially with the cooling fins ( 75 ); said cooling fins surrounding at least a portion ( 73 B) of the intermediate annular casing component ( 73 ).

11 . The gas turbine engine of one or more of the preceding claims, wherein the exhaust gas diffuser ( 65 ) comprises an inner thermal insulation shield ( 79 ), located downstream of the cooling fins ( 75 ) with respect to the combustion gas flow.

12 . The gas turbine engine of claim 11 when depending upon at least one of claims 5 to 7 , wherein the inner thermal insulation shield ( 79 ) is arranged at an inner surface of the diffuser casing portion ( 52 B).

Assignees

• Nuovo Pignone Tecnologie Srl

Inventors

• Lombardi Luca
• Mavuri Rajesh
• Reddy Vishnu Vardhan

Classifications

• F01D25/12 Primary

  Cooling · CPC title

• F05D2260/22141

  using fins or ribs · CPC title

• F01D25/30

  Exhaust heads, chambers, or the like · CPC title

• F01D9/04

  forming ring or sector · CPC title

• F01D25/26

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