Shroud cooling segment and assembly

• US 6,354,795 B1
• Filed: 07/27/2000
• Issued: 03/12/2002
• Est. Priority Date: 07/27/2000
• Status: Expired due to Fees

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Lee, Ching-Pang, White, Gregory Alan
• Primary Examiner(s): Lopez, F. Daniel
• Assistant Examiner(s): McCoy, Kimya N
• Application Number:
  US09/627,050
• Time in Patent Office: 593 Days
• Field of Search: 415/116, 415/115, 415/170.1, 415/185
• US Class Current: 415/116
• 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 25/246 Fastening of diaphragms or stator-rings
• CPC Class Codes: F05D 2240/11 Shroud seal segments

Abstract

A cooling shroud segment for a high pressure turbine that provides improved cooling in the region of the side panels from the midsection thereof forward to the leading edge and particularly in the midsection of the side panel. A shroud subassembly can be formed from a pair of such adjacent shroud segments with opposed adjacent side panels where the spacing of the outlets of the cooling air passages exiting from each of these adjacent side panels are staggered and where the adjacent panels have a spline seal slot with a humped section in at least the midsection of the side panel above and across the outlets of the cooling air passages exiting from the midsection of the side panel, in combination with a spline seal positioned in the gap between the opposed adjacent side panels. This shroud subassembly provides more uniform impingement cooling coverage and localizes more of the cooling air exiting the outlets from these passages in the midsection of the opposed side panels.

Claims

1. A turbine cooling component for a turbine engine, which comprises:

(a) a circumferential leading edge;

(b) a circumferential trailing edge spaced from the leading edge;

(c) an arcuate base connected to the trailing and leading edges and having a back surface and an arcuate inner surface that is in contact with the main hot gas stream of the turbine engine moving in the direction from the leading edge to the trailing edge of the turbine component;

(d) a pair of spaced opposed side panels connected to the leading and trailing edges, each of the side panels having a leading section, a midsection and trailing section;

(e) a plurality of cooling air passages extending through the base from the back surface thereof and having outlets exiting from at least one of the leading edge, the side panels and the inner surface of the base;

(f) wherein all of the plurality of cooling air passages having outlets that exit from the leading or midsections of each side panel are skewed so that cooling air exits therefrom in a direction opposed to the main hot gas stream;

(g) wherein at least one of the plurality of cooling air passages is an impingement cooling air passage, which has an outlet that exits from the midsection of one of the side panels and wherein at least another of the plurality of cooling air passages is an impingement cooling air passage, which has an outlet that exits from the midsection of the other side panel, and

(h) a spline seal slot that extends from the leading section to the trailing section of each side panel, the slot having a humped section in at least the midsection of the side panel that is above and across at least the outlets of the cooling air passages exiting from the midsection of the side panel.

2. The turbine component of claim 1 wherein at least two of the plurality of cooling air passages have outlets that exit from the leading or midsections of each side panel.

3. The turbine component of claim 2 wherein the outlets of the cooling air passages exiting from the leading or midsections of each of the side panels are spaced such that outlets of the cooling air passages exiting from one side panel are staggered relative to the outlets of the cooling air passages exiting from the other side panel.

4. The turbine component of claim 3 wherein the slot having the humped section is at the bottom of the side panel.

5. The turbine component of claim 4 wherein the humped section of the bottom slot curves upwardly before reaching the outlets of the cooling air passages exiting from the side panel, extends above and across all the outlets of the cooling air passages exiting from the side panel and then curves downwardly once past all of the outlets of the cooling air passages exiting from the side panel.

6. The turbine component of claim 5 wherein each of the side panels further has a top spline seal slot spaced from and above the bottom slot, the top slot extending generally from almost the beginning of the leading section to almost the end of the trailing section of each side panel.

7. The turbine component of claim 6 wherein each of the side panels further has an aft spline seal slot connected at its bottom end to the bottom slot at about the juncture of the midsection and the trailing section of the shroud segment and extending generally diagonally and upwardly towards the upper edge of the trailing section.

8. The turbine component of claim 1 which is a high pressure turbine shroud segment.

9. A turbine cooling subassembly for a turbine engine, which comprises:

(a) a pair of adjacent turbine cooling components, each of the turbine components comprising;

(1) a circumferential leading edge;

(2) a circumferential trailing edge spaced from the leading edge;

(3) an arcuate base connected to the trailing and leading edges and having a back surface and an arcuate inner surface that is in contact with the main gas stream of the turbine engine moving in the direction from the leading edge to the trailing edge of the turbine component;

(4) a pair of spaced opposed side panels connected to the leading and trailing edges, each of the side panels having a leading section, a midsection and trailing section;

(5) a plurality of cooling air passages extending through the base from the back surface thereof and having outlets exiting from at least one of the leading edge, the side panels and the inner surface of the base;

(6) wherein all of the plurality of cooling air passages that have outlets that exit from the leading or midsections of each side panel are skewed so that the cooling air exits therefrom in a direction opposed to the main hot gas stream; and

(7) wherein at least one of the plurality of cooling air passages has an outlet that exits from the midsection of each side panel;

(b) wherein opposed adjacent side panels of the pair of turbine components have a gap therebetween and wherein the outlets of cooling air passages exiting from each of the adjacent side panels is spaced such that outlets of each cooling air passage exiting from one of the adjacent panels is not directly opposite the outlets of the cooling air passages exiting from the other of the adjacent panels;

(c) each of the opposed adjacent side panels of the pair of shroud segment having a spline seal slot that extends from the leading section to the trailing section of the side panel, the slot having a humped section in at least the midsection of the side panel that is above and across at least the outlets of the cooling air passages exiting from the midsection of the side panel; and

(d) at least one spline seal positioned in the gap between the opposed adjacent side panels and including a pair of spaced edges having a length and thickness such that each of the edges is capable of being received by the slot of one of the adjacent side panels.

10. The turbine subassembly of claim 9 wherein at least two of the plurality of cooling air passages have outlets that exit from the leading or midsections of each adjacent side panel.

11. The turbine subassembly of claim 10 wherein the slot is at the bottom of each adjacent side panel.

12. The turbine subassembly of claim 11 wherein the humped section of the bottom slot curves upwardly before reaching the outlets of the cooling air passages exiting from each adjacent side panel, extends above and across all the outlets of the cooling air passages exiting from each adjacent side panel and then curves downwardly once past all of the outlets of the cooling air passages exiting from each adjacent side panel.

13. The turbine subassembly of claim 12 wherein each of the adjacent side panels further has a top spline seal slot spaced from and above the bottom slot, the top slot extending generally from almost the beginning of the leading section to almost the end of the trailing section of each adjacent side panel and wherein the at least one spline seal further comprises a top spline seal having a pair of spaced edges having a length and thickness such that each of the edges is capable of being received by the top slot of one of the adjacent side panels.

14. The turbine subassembly of claim 13 wherein each of the adjacent side panels further has an aft spline seal slot connected at its bottom end to the bottom slot having at about the juncture of the midsection and the trailing section of the shroud segment and extending generally diagonally and upwardly towards the upper edge of the trailing section and wherein the at least one spline seal further comprises an aft spline seal having a pair of spaced edges having a length and thickness such that each of the edges is capable of being received by the aft slot of one of the adjacent side panels.

15. The turbine subassembly of claim 9 which is a shroud cooling subassembly for a high pressure turbine and wherein the turbine components are high pressure turbine shroud cooling segments.