Cooling system for three hook ring segment

• US 8,814,507 B1
• Filed: 05/28/2013
• Issued: 08/26/2014
• Est. Priority Date: 05/28/2013
• Status: Active Grant

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Energy Incorporated (Siemens AG)
• Inventors: Eng, Darryl, Lee, Ching-Pang, Patat, Harry, Campbell, Christian X
• Primary Examiner(s): Nguyen, Ninh H
• Application Number:
  US13/903,087
• Time in Patent Office: 455 Days
• Field of Search: 415/173.1, 415/173.4, 415/174.4, 415/213.1, 415/139
• US Class Current: 415/173.1
• CPC Class Codes: F01D 11/24 by selectively cooling-heating stator or rotor components
• CPC Class Codes: F01D 25/12 Cooling
• CPC Class Codes: F01D 25/14 Casings modified therefor double casings F01D25/26
• CPC Class Codes: F01D 25/24 Casings modified for heating or cooling F01D25/14; Casing parts, e.g. diaphragms, casing fastenings casings for rotary machines or engines in general F16M ; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045
• CPC Class Codes: F01D 5/08 Heating, heat-insulating or cooling means specially adapted for radial flow machines or engines F01D5/04
• CPC Class Codes: F05D 2240/11 Shroud seal segments
• CPC Class Codes: F05D 2260/201 by impingement of a fluid

Abstract

A triple hook ring segment including forward, midsection and aft mounting hooks for engagement with respective hangers formed on a ring segment carrier for supporting a ring segment panel, and defining a forward high pressure chamber and an aft low pressure chamber on opposing sides of the midsection mounting hook. An isolation plate is provided on the aft side of the midsection mounting hook to form an isolation chamber between the aft low pressure chamber and the ring segment panel. High pressure air is supplied to the forward chamber and flows to the isolation chamber through crossover passages in the midsection hook. The isolation chamber provides convection cooling air to an aft portion of the ring segment panel and enables a reduction of air pressure in the aft low pressure chamber to reduce leakage flow of cooling air from the ring segment.

Claims

1. A turbine shroud assembly for a gas turbine engine, said turbine shroud assembly comprising:

a ring segment including a ring segment panel comprising a leading edge, a trailing edge and a midsection defined therebetween, said ring segment comprising a forward mounting hook at said leading edge, a midsection mounting hook at said midsection and an aft mounting hook at said trailing edge;

a ring segment carrier circumferentially spanning and supporting said ring segment, said ring segment carrier comprising a forward section, a midsection and an aft section, said forward section forming a forward hanger coupled to said forward mounting hook, said midsection forming a midsection hanger coupled to said midsection mounting hook defining a first leakage path, said aft section forming an aft hanger coupled to said aft mounting hook defining a second leakage path;

a forward impingement cooling chamber defined between said ring segment panel and said ring segment carrier and between said forward mounting hook and said midsection mounting hook;

at least one feed hole extending through said ring segment carrier and configured to meter high pressure cooling air into said forward impingement cooling chamber;

an aft low pressure chamber defined between said ring segment panel and said ring segment carrier and between said midsection hanger and said aft mounting hook, said ring segment carrier substantially preventing cooling air from entering said aft low pressure chamber;

an isolation plate extending between said midsection mounting hook and an aft location adjacent to said ring segment panel defining an isolation chamber radially inward from said aft low pressure chamber between said isolation plate and said ring segment panel; and

a transverse crossover passage formed through said midsection mounting hook providing cooling air from said forward impingement cooling chamber to said isolation chamber, said isolation plate substantially preventing cooling air provided to said isolation chamber from entering said aft low pressure chamber.

2. The turbine shroud assembly of claim 1, including a forward impingement cooling plate extending between said midsection mounting hook and a forward location in said forward impingement cooling chamber, said forward impingement cooling plate including impingement cooling holes and separating said forward impingement cooling chamber into a radially outer cooling chamber supply side and a radially inner impingement cooling side.

3. The turbine shroud assembly of claim 2, wherein cooling air within said supply side of said forward impingement cooling chamber passes through said first leakage path to said low pressure aft chamber, and cooling air within said low pressure aft chamber passes out of said turbine shroud assembly through said second leakage path.

4. The turbine shroud assembly of claim 1, wherein cooling air provided to said isolation chamber is directed into contact with said ring segment panel providing convective cooling to said ring segment panel from a location adjacent said midsection mounting hook to a location adjacent said aft mounting hook.

5. The turbine shroud assembly of claim 1, wherein said isolation plate is sealed to said ring segment panel along axially extending sides of said ring segment panel between said midsection mounting hook and said aft mounting hook.

6. The turbine shroud assembly of claim 1, wherein said transverse crossover passage is located radially inward from a junction of said isolation plate with said midsection mounting hook for effecting transfer of cooling air from said forward impingement cooling chamber to said isolation chamber.

7. The turbine shroud assembly of claim 1, including an aft impingement cooling plate located radially inward from said transverse crossover passage between said isolation plate and said ring segment panel and extending between said midsection mounting hook and an aft location adjacent to said panel, said aft impingement cooling plate including impingement cooling holes providing impingement cooling from said isolation chamber to at least a portion of an outwardly facing surface of said panel.

8. The turbine shroud assembly of claim 7, including a forward impingement cooling plate extending between said midsection mounting hook and a forward location in said forward impingement cooling chamber, said forward and aft impingement cooling plates comprise primary zone cooling plates providing impingement cooling to primary zones of said panel, and including forward and aft secondary impingement cooling plates providing impingement cooling to secondary zones of said panel, wherein respective forward and aft primary and secondary cooling plates form two-step serial cooling paths extending forward and aft of said midsection mounting hook.

9. The turbine shroud assembly of claim 1, including a plurality of axial flow convection cooling channels formed in an outer side of said ring segment panel and having inlet ends adjacent to said midsection hanger hook, said inlet ends receiving cooling air from said isolation chamber.

10. The turbine shroud assembly of claim 1, including one or more axial convective cooling passages extending within said ring segment panel adjacent to axial edges of said panel, each said axial convective cooling passage including an inlet receiving cooling air from said aft low pressure chamber.

11. The turbine shroud assembly of claim 10, including a plurality of convective cooling passages in said panel extending from said forward impingement cooling chamber to said axial edges of said panel, said convective cooling passages located between said midsection mounting hook and said leading edge of said panel.

12. The turbine shroud assembly of claim 1, wherein:

said forward, midsection and aft sections of said ring segment carrier include respective forward, midsection and aft support structure engaged with cooperating structure of a casing for the engine;

a forward high pressure plenum is defined between said forward and midsection support structures for providing said high pressure cooling air through said at least one feed hole; and

an aft low pressure plenum is defined between said midsection and said aft support structures and is substantially isolated from said high pressure cooling air of said forward high pressure plenum.

13. A turbine shroud assembly for a gas turbine engine, said turbine shroud assembly comprising:

a ring segment including a ring segment panel comprising a leading edge, a trailing edge and a midsection defined therebetween, said ring segment comprising a forward mounting hook at said leading edge, a midsection mounting hook at said midsection and an aft mounting hook at said trailing edge;

a ring segment carrier circumferentially spanning and supporting said ring segment, said ring segment carrier comprising a forward section, a midsection and an aft section, said forward section forming a forward hanger coupled to said forward mounting hook, said midsection forming a midsection hanger coupled to said midsection mounting hook defining a first leakage path, said aft section forming an aft hanger coupled to said aft mounting hook defining a second leakage path;

said forward section of said ring segment carrier including a forward support structure engaged with a forward cooperating structure of a casing of the engine, said midsection of said ring segment carrier including a midsection support structure engaged with a midsection cooperating structure of said casing, and said aft section of said ring segment carrier including an aft support structure engaged with an aft cooperating structure of said casing;

a forward high pressure plenum defined between said forward support structure and said midsection support structure for providing high pressure cooling air to a forward impingement cooling chamber defined between said ring segment panel and said ring segment carrier and between said forward mounting hook and said midsection mounting hook;

an aft low pressure plenum defined between said midsection support structure and said aft support structure and substantially isolated from said high pressure cooling air of said forward high pressure plenum;

an aft low pressure chamber defined between said ring segment panel and said ring segment carrier and between said midsection hanger and said aft mounting hook;

an isolation chamber defined radially inward from said aft low pressure chamber between said midsection mounting hook and said aft mounting hook;

a transverse crossover passage connecting said forward impingement cooling chamber to said isolation chamber; and

said isolation chamber substantially isolating said aft low pressure chamber from cooling air provided through said transverse crossover passage to effect a reduction of leakage air through said second leakage path.

14. The turbine shroud assembly of claim 13, wherein a leakage of cooling air passes from said forward impingement cooling chamber to said aft low pressure chamber through said first leakage path, and including one or more flow passages extending from said aft low pressure chamber to a location of lower pressure in fluid communication with a hot gas path through the engine for reducing the pressure in said aft low pressure plenum and further effecting a reduction of leakage air through said second leakage path.

15. The turbine shroud assembly of claim 13, wherein:

said engagement between said aft support structure and said aft cooperating structure of said casing defines a third leakage path of cooling air out of said turbine shroud assembly; and

said engagement between said midsection support structure and said midsection cooperating surface defines a fourth leakage path of cooling air from said forward high pressure plenum to said aft low pressure plenum.

16. The turbine shroud assembly of claim 13, wherein air entering said aft low pressure chamber comprises substantially only leakage air.

17. The turbine shroud assembly of claim 16, wherein air within said aft low pressure chamber comprises a cooling air source for convective cooling passages extending within said ring segment panel.

18. The turbine shroud assembly of claim 17, wherein said convective cooling passages extend axially within said ring segment panel to said trailing edge of said ring segment panel.

19. The turbine shroud assembly of claim 16, wherein air entering said aft low pressure plenum comprises substantially only leakage air.