Industrial gas turbine exhaust system with modular struts and collars

Patent metadata

Field	Value
Publication number	US-9540956-B2
Application number	US-201314087060-A
Country	US
Kind code	B2
Filing date	Nov 22, 2013
Priority date	Nov 22, 2013
Publication date	Jan 10, 2017
Grant date	Jan 10, 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 struts interposed between the outer and inner cases that are tilted at an angle relative to a radius defined by the exhaust system centerline; and
first and second strut collars respectively coupled to respective ends of each strut and its respective abutting outer or inner case, each respective collar outer surface having a constant fillet radius external profile on an acute angle side thereof, for smooth exhaust flow transition between its respective strut and abutting case surface, the fillet radius profile having a range of 15%-40% of strut maximum thickness, each strut collar having a cross section thickness varying by no more than 10% at any circumferential location.

2. The system of claim 1 , the struts having symmetrical airfoil profiles, camber lines of which are aligned parallel with exhaust flow direction in the exhaust path.

3. The system of claim 2 , the airfoil profile having a width to chord length ratio of up to approximately 40% and a trailing edge radius between 10%-20% of the strut chord length.

4. The system of claim 1 , further comprising the inner and outer cases adapted for insertion within a turbine exhaust case (TEC), with the struts oriented downstream of the TEC.

5. The system of claim 4 , the struts oriented in radially aligned rows in the TEC and downstream the TEC.

6. 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; and
an industrial gas turbine exhaust system, having:
a turbine exhaust case (TEC) coupled to a downstream end of the turbine section;
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, extending downstream of the turbine blades;
a plurality of struts interposed between the outer and inner cases that are tilted at an angle relative to a radius defined by the exhaust system centerline; and
first and second strut collars respectively coupled to respective ends of each strut and its respective abutting outer or inner case, each respective collar outer surface having a constant fillet radius external profile on an acute angle side thereof, for smooth exhaust flow transition between its respective strut and abutting case surface, the fillet radius profile having a range of 15%-40% of strut maximum thickness, each strut collar having a cross section thickness varying by no more than 10% at any circumferential location.

7. The apparatus of claim 6 , the plurality of struts axially aligned about the exhaust system circumference downstream of the TEC.

8. The apparatus of claim 7 , the struts downstream of the TEC having symmetrical airfoil profiles, camber lines of which are aligned parallel with exhaust flow direction in the exhaust path.

9. The apparatus of claim 8 , the struts downstream of the TEC forming an airfoil profile having a width to chord length ratio of up to approximately 40% and a trailing edge radius between approximately 10%-20% of the strut chord length.

10. The apparatus of claim 1 , respective strut collar cross section thickness on acute angle circumferential locations thereof being 50%-250% greater than mating inner or outer case thickness.

11. The apparatus of claim 1 , respective strut collar cross section thickness matching that of mating inner or outer case thickness.

12. The apparatus of claim 6 , respective strut collar cross section thickness matching that of mating inner or outer case thickness.

Assignees

• 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

• F02C7/20

  Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title

• F01D25/28

  Supporting or mounting arrangements, e.g. for turbine casing · CPC title

• Y10T29/49231

  I.C. [internal combustion] engine making · CPC title