Modular industrial gas turbine exhaust system

Patent metadata

Field	Value
Publication number	US-9587519-B2
Application number	US-201314087086-A
Country	US
Kind code	B2
Filing date	Nov 22, 2013
Priority date	Nov 22, 2013
Publication date	Mar 7, 2017
Grant date	Mar 7, 2017

Abstract

An integrated single-piece exhaust system (SPEX) with modular construction that facilitates design changes for enhanced aerodynamics, structural integrity or serviceability. The SPEX defines splined or curved exhaust path surfaces, such as a series of cylindrical and frusto-conical sections that mimic curves. The constructed sections may include: (i) a tail cone assembly fabricated from conical sections that taper downstream to a reduced diameter; or (ii) an area-ruled cross section axially aligned with one or more rows of turbine struts; or both features. Modular inner and outer diameter inlet lips enhance transitional flow between the last row blades and the SPEX, as well as enhance structural integrity. Modular strut collars have large radius profiles between the SPEX annular inner diameter and outer diameter flow surfaces, for enhanced airflow and constant thickness walls for uniform heat transfer and thermal expansion. Scalloped mounting flanges enhance structural integrity and longevity.

First claim

What is claimed is:

1. An industrial gas turbine exhaust system, comprising:
an inner case;
an outer case circumscribing the inner case in spaced relationship relative to a centerline defined by the exhaust system;
a turbine exhaust path defined between the outer and inner cases;
a plurality of modular struts interposed between the outer and inner cases, each strut having:
an elongated strut support member;
an inner diameter strut collar coupled to the strut support member and the inner case; and
an outer diameter strut collar coupled to the strut support member and the outer case;
each respective inner and outer diameter strut collar having a generally uniform vertical/radial cross section thickness that is approximately the same as thickness of an adjoining respective outer or inner case on at least a portion of the respective collar circumference, for equalizing heat transfer and thermal deformation throughout the collar;
a tail cone coupled to and projecting axially downstream from the inner case;
a removable tail cone extension for access to gas turbine components covered by the exhaust system when said system is installed on an industrial gas turbine; and
a selectively removable tail cover coupled to a downstream end of the tail cone extension;

the tail cone extension selectively coupled to the tail cone with sector shaped nut plates receiving mating threaded fasteners retained within the tail cone and extension interior that are accessible by removing the tail cover.

2. The system of claim 1 , further comprising:
the struts tilted at an angle relative to a radius defined by the exhaust system centerline; and
the inner diameter strut collar and the outer diameter strut collar each having generally uniform vertical/radial cross section thickness at least on an obtuse angle side of the collar that varies within approximately +/−10%.

3. The system of claim 1 , the inner diameter strut collar and the outer diameter strut collar each comprising metal castings welded to the strut support member and its respective case.

4. The system of claim 1 , the inner diameter strut collar and the outer diameter strut collar each comprising metal forgings welded to the strut support member and its respective case.

5. The system of claim 1 , further comprising a scalloped seal flange on a circumferential surface of one or both of the inner case or outer case for mounting its respective case on the gas turbine.

6. The system of claim 1 , further comprising an outer diameter stiffening ring with a lip extending radially inwardly therefrom into the turbine exhaust path on an inlet side of the outer case, for enhancing exhaust stiffness and/or vibration pulsation resistance.

7. The system of claim 1 , the inner case defining a stiffening ring extending inwardly toward the centerline on an inlet side of the inner case, for enhancing exhaust stiffness and/or vibration pulsation resistance.

8. The system of claim 7 , further comprising a segmented service access cutout having a first removable portion formed in the inner case stiffening ring and a second removable portion formed in the inner case, for accessing gas turbine components covered by the exhaust system when said system is installed on the industrial gas turbine.

9. An industrial gas turbine apparatus, comprising:
a compressor section; a combustor section;
a turbine section including a last downstream row of turbine blades that are mounted on a rotating shaft;
a turbine exhaust case (TEC) coupled to a downstream end of the turbine section; and
the industrial gas turbine exhaust system of claim 1 coupled to the TEC.

10. An industrial gas turbine exhaust system, comprising:
an inner case;
an outer case circumscribing the inner case in spaced relationship relative to a centerline defined by the exhaust system;
a turbine exhaust path defined between the outer and inner cases;
a plurality of struts interposed between the outer and inner cases; and
the inner case defining on an inlet side thereof a stiffening ring extending inwardly toward the centerline, for enhancing exhaust stiffness and/or vibration pulsation resistance, and for enhancing non-turbulent airflow transition through the exhaust path;
a tail cone coupled to and projecting axially downstream from the inner case;
a removable tail cone extension for access to gas turbine components covered by the exhaust system when said system is installed on an industrial gas turbine; and
a selectively removable cover coupled to a downstream end of the tail cone extension;
the tail cone extension selectively coupled to the tail cone with sector shaped nut plates receiving mating threaded fasteners retained within the tail cone and extension interior that are accessible by removing the cover.

11. The system of claim 10 , the outer case defining on an inlet side thereof an outer diameter stiffening ring with a lip extending radially inwardly therefrom into the turbine exhaust path, for enhancing exhaust stiffness and/or vibration pulsation resistance, and for enhancing non-turbulent airflow transition through the exhaust path.

12. The system of claim 10 , further comprising a segmented service access cutout having a first removable portion formed in the inner stiffening ring and a second removable portion formed in the inner case, for accessing gas turbine components covered by the exhaust system when said system is installed on the industrial gas turbine.

13. The system of claim 10 , further comprising a scalloped seal flange on a circumferential surface of one or both of the inner case or outer case for mounting its respective case on the gas turbine.

14. An industrial gas turbine apparatus, comprising:
a compressor section;
a combustor section;
a turbine section including a last downstream row of turbine blades that are mounted on a rotating shaft;
a turbine exhaust case (TEC) coupled to a downstream end of the turbine section; and
the industrial gas turbine exhaust system of claim 10 coupled to the TEC.

15. An industrial gas turbine exhaust system, comprising:
an inner case;
an outer case circumscribing the inner case in spaced relationship relative to a centerline defined by the exhaust system;
a turbine exhaust path defined between the outer and inner cases;
a plurality of struts interposed between the outer and inner cases; and
the outer case defining on an inlet side thereof an outer diameter stiffening ring with a lip extending radially inwardly therefrom into the turbine exhaust path, for enhancing exhaust stiffness and/or vibration pulsation resistance, and for enhancing non-turbulent airflow transition through the exhaust path;
a tail cone coupled to and projecting axially downstream from the inner case;
a removable tail cone extension for access to gas turbine components covered by the exhaust system when said system is installed on an industrial gas turbine; and
a selectively removable cover coupled to a downstream end of the tail cone extension;
the tail cone extension selectively coupled to the tail cone with sector shaped nut plates receiving mating threaded fasteners retained within the tail cone and extension interior that are accessible by removing the cover.

16. The system of claim 15 , further comprising a scalloped seal flange on a circumferential surface of one or both of the inner case or outer case for mounting its respective case on the gas turbine.

17. An industrial gas turbine apparatus, comprising:
a compressor section;
a combustor section;
a turbine section including a last downstream row of turbine

Assignees

• Salunkhe Anil L
• Orosa John A
• Shteyman Yevgeniy
• Porter Matthew R
• Han Lijuan
• Delisa Iii Matthew J
• Riveros Daniel F
• Siemens Energy Inc

Inventors

• Salunkhe Anil L
• Orosa John A
• Shteyman Yevgeniy
• Porter Matthew R
• Han Lijuan
• Delisa Iii Matthew J
• Riveros Daniel F

Classifications

• F01D25/30 Primary

  Exhaust heads, chambers, or the like · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2250/232

  conical · CPC title

• F05D2230/51

  in a modular way, e.g. using several identical or complementary parts or features · CPC title

• F01D25/162

  Bearing supports · CPC title