Turbine combustion system liner

Patent metadata

Field	Value
Publication number	US-8955330-B2
Application number	US-201113212248-A
Country	US
Kind code	B2
Filing date	Aug 18, 2011
Priority date	Mar 29, 2011
Publication date	Feb 17, 2015
Grant date	Feb 17, 2015

Abstract

A combustion chamber liner ( 41 ) with a forward section ( 44 ) and an aft section ( 46 ). The aft section has an array of aft axial cooling fins ( 62 ) covered by a tubular support ring ( 52 ), thus forming an array of aft axial grooves ( 66 ) between the aft axial fins. Inlet holes ( 54 ) in the front end of the support ring may admit coolant ( 37 ) into an upstream end of the aft axial cooling fins. An impingement plenum ( 61 ) may receive the coolant just before the aft axial cooling fins. Each aft axial fin may include a plurality of axially spaced bumpers ( 64 ) that contact the support ring. Spaces or grooves ( 68 ) between the bumpers provide circumferential cross flow of coolant between the grooves. The aft axial grooves may discharge the coolant as film cooling along the inner wall ( 76 ) of a transition duct ( 28 ).

First claim

The invention claimed is:

1. A turbine combustion chamber liner comprising:
a forward wall section having a first outer surface;
an aft wall section connected with the forward wall section, the aft wall section having a second outer surface;
a first array of axial cooling fins formed on the first outer surface;
a second array of axial cooling fins formed on the second outer surface; and
a cylindrical support ring covering the second array of axial cooling fins, the cylindrical support ring comprising a plurality of inlet holes formed along an external surface of the cylindrical support ring for admitting a coolant onto grooves formed between axial cooling fins within the second array of axial cooling fins.

2. The turbine combustion chamber liner of claim 1 further comprising:
the first array of axial cooling fins being formed straight along a longitudinal axis of the turbine combustion chamber liner and being spaced around the circumference of the first outer surface with the first array of axial cooling fins devoid of turbulators.

3. The turbine combustion chamber liner of claim 2 further comprising fins within the first array of axial cooling fins being separated by respective grooves devoid of turbulators.

4. The turbine combustion chamber liner of claim 3 further comprising
the second array of axial cooling fins formed straight along the longitudinal axis of the turbine combustion chamber liner and being spaced around the circumference of the second outer surface with the second array of axial cooling fins devoid of turbulators; and
the plurality of inlet holes formed around a forward end of the cylindrical support ring for admitting the coolant onto grooves formed between axial cooling fins within the second array of axial cooling fins.

5. The turbine combustion chamber liner of claim 4 further comprising an impingement plenum formed between the cylindrical support ring and the second outer surface forward of the second array of axial cooling fins, wherein the plurality of inlet holes admit the coolant into the impingement plenum, which then flows onto the grooves formed between fins within the second array of axial cooling fins.

6. A turbine combustion chamber liner comprising:
a tubular wall having a forward section and an aft section;
a first array of axial cooling fins formed on an outer surface of the aft section;
a plurality of respective grooves formed between cooling fins within the first array of axial cooling fins;
a tubular support ring covering the first array of axial cooling fins;
a plurality of coolant inlet holes formed within a forward end of the tubular support ring for admitting a coolant onto the first array of axial cooling fins and the plurality of respective grooves; and
wherein the first array of axial cooling fins and the plurality of respective grooves are formed straight along a longitudinal axis of the tubular wall having smooth surfaces devoid of turbulators.

7. The turbine combustion chamber liner of claim 6 further comprising a plurality of axially spaced bumpers formed on the first array of axial cooling fins that support the tubular support and wherein an aft end of each of the plurality of respective grooves is open for discharging the coolant.

8. The turbine combustion chamber liner of claim 7 further comprising a plurality of circumferential grooves formed between the plurality of axially spaced bumpers wherein the plurality of circumferential grooves are shallower than the plurality of respective grooves.

9. The turbine combustion chamber liner of claim 6 further comprising:
a second array of axial cooling fins formed on an outer surface of the forward section; and
wherein the second array of axial cooling fins are formed straight along the longitudinal axis of the tubular wall having smooth surfaces devoid of turbulators.

10. The turbine combustion chamber liner of claim 9 further comprising an impingement plenum formed between the tubular support ring and a forward end of the aft section wherein the plurality of coolant inlet holes admit the coolant into the impingement plenum, which then flows over the plurality of respective grooves.

11. The turbine combustion chamber liner of claim 10 further comprising a transition duct having a forward end that encircles and seals against the tubular support ring wherein an aft end of the plurality of respective grooves opens proximate an inner surface of the transition duct so that the coolant provides film cooling against the inner surface of the transition duct when discharged from the plurality of respective grooves.

12. The turbine combustion chamber liner of claim 6 further comprising the forward section formed as a forward conical tubular segment and a middle conical tubular segment and the aft section formed as an aft cylindrical tubular segment.

13. The turbine combustion chamber liner of claim 6 further comprising:
the first array of axial cooling fins extending around a circumference of the aft section;
a second array of axial cooling fins formed on an outer surface of the forward section and extending around a circumference of the forward section, the second array of axial cooling fins formed straight along the longitudinal axis of the tubular wall having smooth surfaces devoid of turbulators; and
an impingement plenum formed between the tubular support ring and a forward end of the aft section wherein the coolant may flow through the plurality of coolant inlet holes into the impingement plenum and over the plurality of respective grooves so that the coolant exits a downstream end of the aft section.

14. A turbine combustion chamber section comprising:
an outer surface defining a circumference of the section;
a plurality of axial cooling fins formed on the outer surface, the plurality of axial cooling fins extending substantially parallel to a longitudinal axis of the section and having smooth surfaces devoid of turbulators; and
a plurality of longitudinal grooves formed between ones of the plurality of axial cooling fins, the plurality of longitudinal grooves having smooth surfaces devoid of turbulators whereby a coolant flowing over the outer surface convectively cools the section;
a plurality of bumpers formed on ones of the plurality of axial cooling fins; and
circumferential grooves formed between ones of the plurality of bumpers whereby the coolant may flow both axially along the plurality of longitudinal grooves and circumferentially among the plurality of longitudinal grooves by passing through the circumferential grooves.

15. The turbine combustion chamber section of claim 14 further comprising:
a support ring affixed over the plurality of axial cooling fins and the plurality of longitudinal grooves, at least a portion of the plurality of bumpers having a height sufficient to support the support ring.

16. The turbine combustion chamber section of claim 15 further comprising the circumferential grooves formed shallower than the plurality of longitudinal grooves.

17. The turbine combustion chamber section of claim 15 further comprising a transition duct having a forward end that encircles and seals against the support ring wherein an aft end of each of the plurality of longitudinal grooves opens proximate an inner surface of the transition duct to film cooling the inner surface.

18. The turbine combustion chamber section of claim 17 further comprising:
an impingement plenum formed between a forward end of the support ring and a forward end of the outer surface; and
a plurality of coolant inlet holes formed above

Assignees

• Narcus Andrew R
• Negron-Sanchez Kristel
• Pula John
• Therrien Neal
• Siemens Energy Inc

Inventors

• Narcus Andrew R
• Negron-Sanchez Kristel
• Pula John
• Therrien Neal

Classifications

• F23R3/005

  Combined with pressure or heat exchangers · CPC title

• F23R2900/03043

  Convection cooled combustion chamber walls with means for guiding the cooling air flow · CPC title

• F23R3/002 Primary

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title