Gas turbine row #1 steam cooled vane

• US 6,019,572 A
• Filed: 08/06/1998
• Issued: 02/01/2000
• Est. Priority Date: 08/06/1998
• Status: Expired due to Term

• Current Assignee: Siemens Westinghouse Power Corporation
• Original Assignee: Siemens Westinghouse Power Corporation
• Inventors: Cunha, Frank J.
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): MCDOWELL, LIAM J
• Application Number:
  US09/129,904
• Time in Patent Office: 544 Days
• Field of Search: 415/114, 415/115, 415/116, 415/176, 415/178, 416/95, 416/96 R, 416/97 R, 416/96 A
• US Class Current: 415/114
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F01D 9/065 Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids see also F01D25/16, F01D25/24 and F01D25/26
• CPC Class Codes: F05D 2240/81 Cooled platforms
• CPC Class Codes: F05D 2260/205 Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes

Abstract

A design for a vane segment having a closed-loop steam cooling system is provided. The vane segment comprises an outer shroud, an inner shroud and an airfoil, each component having a target surface on the inside surface of its walls. A plurality of rectangular waffle structures are provided on the target surface to enhance heat transfer between each component and cooling steam. Channel systems are provided in the shrouds to improve the flow of steam through the shrouds. Insert legs located in cavities in the airfoil are also provided. Each insert leg comprises outer channels located on a perimeter of the leg, each outer channel having an outer wall and impingement holes on the outer wall for producing impingement jets of cooling steam to contact the airfoil'"'"'s target surface. Each insert leg further comprises a plurality of substantially rectangular-shaped ribs located on the outer wall and a plurality of openings located between outer channels of the leg to minimize cross flow degradation.

Claims

1. In a turbine, a vane segment having a closed-loop steam cooling system, the vane segment comprising:

an outer shroud comprising;

an outer platform having a target surface on an inside surface of walls of said outer platform exposed to a working gas of the turbine;

outer railings, which are situated along edges of said outer platform;

a plurality of rectangular waffle structures on the target surface to enhance heat transfer between said outer shroud and cooling steam;

an outer cover positioned on said outer railings;

an outer impingement plate situated between said cover and said platform to form (i) an outer plenum between said outer impingement plate and said outer cover, and (ii) a relatively small space between said outer impingement plate and said outer platform, said outer impingement plate having a plurality of impingement holes for producing impingement jets of cooling steam to contact the target surface of said outer platform;

at least one inlet situated on said outer cover for providing cooling steam to the vane segment; and

at least one outlet situated on said outer cover for exhausting steam;

an inner shroud comprising;

an inner platform having a target surface on an inside surface of walls of said inner platform exposed to the working gas of the turbine;

inner railings situated along edges of said inner platform;

a plurality of rectangular waffle structures on the target surface of said platform to enhance heat transfer between said inner shroud and the cooling steam;

an inner cover positioned on said inner railings; and

an inner impingement plate situated between said inner cover and said inner platform to form (i) an inner plenum between said inner impingement plate and said inner cover, and (ii) a relatively small space between said inner impingement plate an a said inner platform, said inner impingement plate having a plurality of impingement holes for producing impingement jets of cooling steam to contact the target surface of said inner platform; and

an airfoil having a first end connected to said outer platform and a second end connected to said inner platform, said airfoil comprising;

walls having a target surface on an inside surface of said walls exposed to the working gas of the turbine;

a plurality of rectangular waffle structures on the target surface of said walls to enhance heat transfer between said airfoil and the cooling steam; and

at least one cavity to serve as a passageway for cooling steam to flow between said outer shroud and said inner shroud.

2. The vane segment of claim 1, wherein said outer shroud further comprises:

a first outer channel system in said outer railings comprising passageways for steam to flow through said outer railings;

at least one hole to provide a passageway for steam to flow into said outer railings from the space between said outer impingement plate and said outer platform;

a second outer channel system on said outer platform for exhausting steam, said second channel comprising

at least one channel for providing a passageway for steam to reach said outlet from said outer railings; and

at least one link between said outer railings and said second outer channel system for steam to flow from said outer railings to said second outer channel system;

wherein said inner shroud further comprises;

a first inner channel system in said inner railings comprising passageways for steam to flow through said inner railings;

at least one hole to provide a passageway for steam to flow into said inner railings from the space between said inner impingement plate and said inner platform;

a second channel system on said inner platform for exhausting steam, said second channel system comprising

at least one channel for providing a passageway for steam to reach said outlet from said outer railings; and

at least one link between said inner railings and said second channel system for steam to flow from said inner railings to said second channel system.

3. The vane segment of claim 2, wherein said outer railings and said inner railings each have a bottom surface with ridges to enhance heat transfer.

4. The vane segment of claim 1, wherein said airfoil further comprises an insert leg located in said cavity, said insert leg comprising:

a perimeter and a substantial center; and

at least one outer channel located on said perimeter, said outer channel having an outer wall and impingement holes on said outer wall for producing impingement jets of cooling steam to contact the target surface.

5. The vane segment of claim 4, wherein said insert leg further comprises:

a plurality of ribs of substantially rectangular shape and located on said outer wall disposed in horizontal and vertical orientation and extending between said outer wall and the target surface of said walls of said airfoil, said ribs serving to minimize cross flow degradation of the steam.

6. The vane segment of claim 5, wherein said insert leg further comprises:

at least two outer channels;

at least one center channel located in said substantial center of said insert leg; and

a plurality of openings located between said outer channels to minimize cross flow degradation by providing a passageway for the cross flow between the target surface and said outer walls of said outer channels to flow into said center channel.

7. The vane segment of claim 6, wherein said airfoil further comprises:

at least one structural rib extending from said outer shroud to said inner shroud;

at least two cavities formed by said at least one structural rib;

at least two insert legs, one located inside each cavity; and

a plurality of openings located between said insert legs to minimize cross flow degradation by providing a passageway for the cross flow between the target surface and said outer walls of said outer channels to flow into said center channel.

8. The vane segment of claim 7, wherein said airfoil further comprises:

a leading edge and a trailing edge, whereby at least one cavity is located at said leading edge of said airfoil and at least one cavity is located at said trailing edge of said airfoil;

wherein in said insert leg in said at least one cavity at said leading edge;

said at least one center channel is closed at said outer shroud and open at said inner shroud; and

said at least two outer channels are open at said outer shroud and closed at said inner shroud;

whereby the cooling steam enters said insert legs at said outer shroud through said at least two outer channels and exits said insert legs at said inner shroud through said at least one center channel; and

wherein in said insert leg in said at least one cavity at said trailing edge;

said at least one center channel is open at said outer shroud and closed at said inner shroud; and

said at least two outer channels are closed at said outer shroud and open at said inner shroud;

whereby the cooling steam enters said at least one insert leg at said trailing edge at said inner shroud through said at least two outer channels and exits said at least one insert leg at said trailing edge at said outer shroud through said at least one center channel.

9. The vane segment of claim 8 further comprising a conduit extending from said outer cover to the inner plenum for supplying cooling steam directly into the inner plenum, said conduit passing through said at least one center channel of said insert leg in said at least one cavity at said leading edge of said airfoil.

10. The vane segment of claim 1, wherein the airfoil further comprises:

a leading edge and a trailing edge;

a plurality of structural ribs extending from said outer shroud to said inner shroud;

at least one cavity at said leading edge of said airfoil; and

one cavity at said trailing edge of said airfoil;

wherein said outer shroud further comprises;

a first inlet proximate said leading edge;

a second inlet proximate said trailing edge;

a first bevel surrounding said at least one cavity at said leading edge to smooth out an entrance to said at least one cavity through which the cooling steam passes after entering the outer shroud through said first inlet; and

a second bevel surrounding said one cavity at said trailing edge to smooth out an entrance to said one cavity through which the cooling steam passes after entering the outer shroud through said second inlet.

11. The vane segment of claim 10, wherein said one cavity at said trailing edge of said airfoil has a triangular cross-section having a base and an apex, said cavity further comprises:

obstructions situated at the base of the triangle and throughout a length of said cavity to increase resistance in that area and divert steam toward the apex of said cavity.

12. The vane segment of claim 10, wherein said second inlet further comprises a channel to direct some of the cooling steam into said outer railings of said outer shroud to help cool said trailing edge of said outer shroud.

13. The vane segment of claim 1, wherein said outlet further comprises a transition piece in the form of a bellows to allow for effects of thermal expansion.

14. The vane segment of claim 1, wherein said outer cover is welded to said outer railings and pins disposed through said outer cover and said outer railings are used to mechanically join said outer cover to said outer railings.