Industrial gas turbine exhaust system with area ruled exhaust path

Patent metadata

Field	Value
Publication number	US-9512740-B2
Application number	US-201314087050-A
Country	US
Kind code	B2
Filing date	Nov 22, 2013
Priority date	Nov 22, 2013
Publication date	Dec 6, 2016
Grant date	Dec 6, 2016

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:
a turbine exhaust case (TEC) adapted for coupling to a downstream end of a turbine section of an industrial gas turbine;
an inner case coupled to the TEC;
an outer case circumscribing the inner case in spaced relationship relative to a common centerline defined there between, coupled to the TEC;
a turbine exhaust path defined between the outer and inner cases; and
a plurality of tilted struts, oriented downstream of the TEC, interposed within the turbine exhaust path between the outer and inner cases, which are tilted at an angle relative to a radius defined by the common centerline; and
a circumferential profile of at least one of the inner or outer cases forming an area ruled turbine exhaust path cross section proximal the plurality of tilted struts, formed with at least a pair of opposed frusto-conical profile annular sections, in order to compensate for at least a portion of strut reduction in turbine exhaust path cross section.

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

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

4. The system of claim 3 , further comprising respective strut collars coupled to respective ends of each tilted strut and respective abutting outer or inner case, each strut collar defining a strut collar outer surface having a constant fillet radius external profile on an acute angle side thereof for smooth exhaust flow transition between its respective tilted strut and abutting case surface, the constant fillet radius external profile having a range of 15%-40% of tilted strut maximum thickness.

5. The system of claim 1 , the plurality of tilted struts oriented in a radially aligned row in the TEC and in a tilted row downstream the TEC.

6. The system of claim 5 , further comprising respective strut collars coupled to respective ends of each strut and respective abutting outer or inner case, each strut collar defining a strut collar outer surface having a constant fillet radius external profile on an acute angle side thereof for smooth exhaust flow transition between its respective tilted strut and abutting case surface, the constant fillet radius external profile having a range of 15%-40% of tilted strut maximum thickness.

7. 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 common centerline defined there between;
a turbine exhaust path defined between the outer and inner cases, extending downstream of the last downstream row of turbine blades;
a plurality of tilted struts, oriented downstream of the TEC, interposed within the turbine exhaust path between the outer and inner cases, which are tilted at an angle relative to a radius defined by the common centerline; and
a circumferential profile of at least one of the inner or outer cases forming an area ruled turbine exhaust path cross section proximal the plurality of tilted struts, formed with at least a pair of opposed frusto-conical profile annular sections, in order to compensate for at least a portion of strut reduction in turbine exhaust path cross section.

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

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

10. The apparatus of claim 9 , further comprising respective strut collars coupled to respective ends of each tilted strut and respective abutting outer or inner case, each strut collar defining a strut collar outer surface having a constant fillet radius external profile on an acute angle side thereof for smooth exhaust flow transition between its respective tilted strut and abutting case surface, the constant fillet radius external profile having a range of 15%-40% of tilted strut maximum thickness.

Assignees

• Orosa John A
• Hinklein Angelina
• Siemens Energy Inc

Inventors

• Orosa John A
• Hinklein Angelina

Classifications

• F01D25/30 Primary

  Exhaust heads, chambers, or the like · CPC title

• F01D25/243

  Flange connections; Bolting arrangements (F01D25/265 takes precedence) · CPC title

• Y10T29/49234

  Rotary or radial engine making · CPC title

• F05D2250/15

  spiral · CPC title

• F01D9/041

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