Venturi effect endwall treatment

Patent metadata

Field	Value
Publication number	US-10041500-B2
Application number	US-201514962103-A
Country	US
Kind code	B2
Filing date	Dec 8, 2015
Priority date	Dec 8, 2015
Publication date	Aug 7, 2018
Grant date	Aug 7, 2018

Abstract

A gas turbine engine endwall treatment includes a recirculation passages distributed circumferentially around and extending generally axially in an endwall or shroud, Venturi effect producing main throats between main inlet and outlet passages including main inlet and outlet ports respectively extending through the endwall or shroud, and main inlet ports axially aft and downstream of the main outlet ports. Second inlet passages may connect second inlet ports in endwall to main recirculation passages at or near main throats and second inlet ports. An annular groove in endwall may pass through and interconnect the second inlet ports. Two or more clustered inlet passages may extend from two or more clustered secondary inlet ports to two or more intersections of the two or more clustered inlet passages and the main recirculation passage. The main inlet and outlet ports may be spaced one or more stages apart.

First claim

What is claimed is:

1. A gas turbine engine endwall treatment comprising:
a plurality of main recirculation passages distributed circumferentially around and extending generally axially in an endwall or shroud,
each of the main recirculation passages including a Venturi effect producing main throat disposed between a main inlet passage and a main outlet passage,
main inlet and outlet ports of the main inlet and outlet passages respectively extending through the endwall or shroud, and
the main inlet port located axially aft and downstream of the main outlet port in each of the main recirculation passages;
further comprising second inlet passages connecting second inlet ports in the endwall or the shroud to the main recirculation passages at or near to the main throats and the second inlet ports distributed in a circular row around the endwall or the shroud.

2. The endwall treatment as claimed in claim 1 further comprising second throats disposed in the second inlet passages at or near intersections of the second inlet passages and the main recirculation passages.

3. The endwall treatment as claimed in claim 1 further comprising an annular groove in the shroud or endwall and passing through and interconnecting the second inlet ports distributed circumferentially around the endwall or the shroud.

4. A gas turbine engine endwall treatment comprising:
a plurality of main recirculation passages distributed circumferentially around and extending generally axially in an endwall or shroud,
each of the main recirculation passages including a Venturi effect producing main throat disposed between a main inlet passage and a main outlet passage,
main inlet and outlet ports of the main inlet and outlet passages respectively extending through the endwall or shroud, and
the main inlet port located axially aft and downstream of the main outlet port in each of the main recirculation passages;
further comprising two or more clustered inlet passages extending from two or more clustered secondary inlet ports to two or more intersections of the two or more clustered inlet passages respectively and the main recirculation passage in the shroud or endwall.

5. The endwall treatment as claimed in claim 4 , further comprising the two or more clustered inlet passages extending from the two or more clustered secondary inlet ports to two or more clustered secondary throats at or near the two or more intersections of the two or more clustered inlet passages respectively and the main recirculation passage in the shroud or endwall.

6. The endwall treatment as claimed in claim 4 , further comprising two or more annular grooves in the shroud or endwall and the two or more annular grooves passing through and interconnecting the second inlet ports distributed circumferentially around the endwall or the shroud in circular rows of the second inlet ports respectively.

7. A gas turbine engine compressor stage comprising:
a circular row of compressor blades including axially spaced apart leading and trailing edges and airfoils extending radially outwardly to blade tips,
an endwall including a shroud circumscribing the blade tips and the tips generally radially located in close proximity to the endwall and the shroud,
an endwall treatment located in the endwall and including a plurality of main recirculation passages or passages distributed circumferentially around and extending generally axially in an endwall or shroud,
Venturi effect producing main throats disposed between main inlet and outlet passages including main inlet and outlet ports respectively extending through the endwall or shroud,
the main inlet ports located axially aft and downstream of the blade tips and the main outlet ports located axially forward and upstream of the blade tips, and
the main inlet ports located axially aft and downstream of the main outlet ports in the main recirculation passages;
further comprising second inlet passages connecting a circular row of second inlet ports in the endwall or the shroud to the main recirculation passages at or near to the main throats.

8. The gas turbine engine compressor stage as claimed in claim 7 , further comprising second throats disposed in the second inlet passages at or near intersections of the second inlet passages and the main recirculation passages.

9. The gas turbine engine compressor stage as claimed in claim 7 , further comprising an annular groove in the shroud or endwall and passing through and interconnecting the second inlet ports distributed circumferentially around the endwall or the shroud.

10. A gas turbine engine compressor stage comprising:
a circular row of compressor blades including axially spaced apart leading and trailing edges and airfoils extending radially outwardly to blade tips,
an endwall including a shroud circumscribing the blade tips and the tips generally radially located in close proximity to the endwall and the shroud,
an endwall treatment located in the endwall and including a plurality of main recirculation passages or passages distributed circumferentially around and extending generally axially in an endwall or shroud,
Venturi effect producing main throats disposed between main inlet and outlet passages including main inlet and outlet ports respectively extending through the endwall or shroud,
the main inlet ports located axially aft and downstream of the blade tips and the main outlet ports located axially forward and upstream of the blade tips, and
the main inlet ports located axially aft and downstream of the main outlet ports in the main recirculation passages;
further comprising two or more clustered inlet passages extending from two or more clustered secondary inlet ports to two or more intersections of the two or more clustered inlet passages respectively and the main recirculation passage in the shroud or endwall.

11. The gas turbine engine compressor stage as claimed in claim 10 , further comprising the two or more clustered inlet passages extending from the two or more clustered secondary inlet ports to two or more clustered secondary throats at or near the two or more intersections of the two or more clustered inlet passages respectively and the main recirculation passage in the shroud or endwall.

12. The gas turbine engine compressor stage as claimed in claim 10 , further comprising two or more annular grooves in the shroud or endwall and the two or more annular grooves passing through and interconnecting the second inlet ports distributed circumferentially around the endwall or the shroud in circular rows of the second inlet ports respectively.

13. A gas turbine engine compressor assembly comprising:
upstream and downstream stages including upstream and downstream stage blades,
the upstream and downstream stage blades including axially spaced apart leading and trailing edges and airfoils extending radially outwardly to blade tips,
an endwall including shrouds circumscribing the blade tips and the tips generally radially located in close proximity to the endwall and the shrouds,
an endwall treatment located in the endwall and including a plurality of main recirculation passages distributed circumferentially around and extending generally axially in an endwall or shroud,
Venturi effect producing main throats disposed between main inlet and outlet passages including main inlet and outlet ports respectively extending through the endwall or shroud,
the main inlet ports located axially aft and downstream of the blade tips of the downstream stage blades and the main outlet ports located axially forward and upstream of the blade tips of the upstream stage blades, and
the main inlet ports located axially aft

Assignees

• Gen Electric

Inventors

• Streit Josef Anton

Classifications

• F04D29/681

  especially adapted for elastic fluid pumps · CPC title

• F04D29/526

  Details of the casing section radially opposing blade tips (ducts F04D29/545) · CPC title

• F04D29/324

  Blades · CPC title

• F01D9/023 Primary

  Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings · CPC title

• F05D2270/101

  Compressor surge or stall · CPC title