Grooved shroud casing treatment for high pressure compressor in a turbine engine

Patent metadata

Field	Value
Publication number	US-10648484-B2
Application number	US-201715431890-A
Country	US
Kind code	B2
Filing date	Feb 14, 2017
Priority date	Feb 14, 2017
Publication date	May 12, 2020
Grant date	May 12, 2020

Abstract

A compressor for a turbine engine includes a shroud having a grooved section including a plurality of groove segments extending radially into a shroud surface. A rotor assembly rotatably supported in the shroud includes a rotor hub and a plurality of rotor blades. Each rotor blade extends radially from the rotor hub and terminates at a blade tip, which is spaced from the shroud surface by a tip gap and defines a non-constant clearance region between a leading edge position and a medial chord position along the blade chord at the minimum tip clearance. The rotor blades generate an aft axial fluid flow through the shroud and the grooved section is formed in the shroud surface upstream of the medial chord position within the non-constant clearance region for resisting a reverse axial fluid flow through the tip gap when the compressor section is operated at near stall conditions.

First claim

We claim:

1. A turbomachine comprising:
a first turbomachinery component rotatable relative to a second turbomachinery component to generate an aft axial fluid flow therein, wherein a tip gap formed between the first turbomachinery component and a surface adjacent the first turbomachinery component on the second turbomachinery component includes a non-constant clearance region between a first position at a leading edge on the first turbomachinery component and a second position having a minimum tip gap clearance downstream of the first position in an aft axial fluid flow direction; and
a grooved section including a plurality of groove segments extending radially into the surface in the non-constant clearance region for resisting a reverse axial fluid flow through the tip gap,
wherein the grooved section terminates at a last segment in the aft axial fluid flow direction, and wherein the last segment is upstream of the second position.

2. The turbomachine according to claim 1 , wherein the last segment projects to a point that is 40% of a tip chord from the leading edge on the first turbomachinery component.

3. The turbomachine according to claim 1 , wherein the depth of the plurality of groove segments is at least 3 times the minimum tip gap clearance in the non-constant clearance region.

4. The turbomachine according to claim 1 , wherein a depth of the plurality of groove segments is between 3 times and 20 times of a tip gap crown, wherein the tip gap crown is defined as the difference between the minimum tip gap clearance and a maximum tip gap clearance upstream of the minimum tip clearance in the tip gap.

5. The turbomachine according to claim 4 , wherein the depth of the plurality of groove segments is between 5 times and 15 times of the tip gap crown.

6. The turbomachine according to claim 1 , wherein the plurality of groove segments comprises a plurality of saw-tooth groove segments, each saw-tooth groove segment having a leading surface which is perpendicular to the aft axial flow direction and a trailing surface extending from the leading surface to the surface formed on the second turbomachinery component.

7. The turbomachine according to claim 6 , wherein the plurality of groove segments are arranged to form a continuous serration having no intervening surface.

8. The turbomachine according to claim 1 , wherein the grooved section begins at a first segment in the aft axial fluid flow direction, and wherein the first segment is upstream of a leading edge of the first turbomachinery component such that at least a portion of the groove section extends in front of the tip gap.

9. A compressor section for a gas turbine engine comprising:
a housing with a shroud surface having a grooved section including a plurality of groove segments extending radially into the shroud surface; and
a rotor assembly rotatably supported within the housing, the rotor assembly including a rotor hub and a plurality of rotor blades extending radially from the rotor hub and terminating at a blade tip spaced from the shroud surface by a tip gap and defining a non-constant clearance region between a first position at a leading edge on the rotor blade and a second position having a minimum tip gap clearance downstream of the first position in an aft axial fluid flow direction;
wherein the rotor blades generate an aft axial fluid flow in the housing and the grooved section is formed in the shroud surface in the non-constant clearance region for resisting a reverse axial fluid flow through the tip gap,
wherein the grooved section terminates at a last segment in the aft axial fluid flow direction, and wherein the last segment is upstream of the second position.

10. The compressor section according to claim 9 , wherein the last segment projects to a point that is 40% of a tip chord from the leading edge on the rotor blade.

11. The compressor section according to claim 9 , wherein the depth of the plurality of groove segments is at least 3 times the minimum tip gap clearance in the non-constant clearance region.

12. The compressor section according to claim 9 , wherein a depth of a groove segment is between 3 times and 20 times of a tip gap crown, wherein the tip gap crown is defined as the difference between the minimum tip gap clearance and a maximum tip gap clearance upstream of the minimum tip gap clearance.

13. The compressor section according to claim 12 , wherein the depth of the groove segment is between 5 times and 15 times of the tip gap crown.

14. The compressor section according to claim 9 , wherein the groove section comprises a plurality of saw-tooth segments, each saw-tooth segment having a leading surface which is generally perpendicular to the aft axial flow direction and a trailing surface extending from the leading surface to the surface formed on the second turbomachinery component.

15. The compressor section according to claim 14 , wherein the plurality of groove segments are arranged to form a continuous serration having no intervening shroud surface.

16. The compressor section according to claim 9 , wherein the grooved section begins at a first segment in the aft axial fluid flow direction, and wherein first segment is upstream of a leading edge of the rotor blades such that at least a portion of the grooved section extends in front of the tip gap.

17. A turbomachine comprising:
a first turbomachinery component rotatable relative to a second turbomachinery component to generate an aft axial fluid flow therein, wherein a tip gap formed between the first turbomachinery component and a surface adjacent the first turbomachinery component on the second turbomachinery component includes a non-constant clearance region between a first position at a leading edge on the first turbomachinery component and a second position having a minimum tip gap clearance downstream of the first position in an aft axial fluid flow direction; and
a grooved section including a plurality of groove segments extending radially into the surface in the non-constant clearance region for resisting a reverse axial fluid flow through the tip gap
wherein the depth of the plurality of groove segments is at least 3 times the minimum tip gap clearance in the non-constant clearance region.

Assignees

• Honeywell Int Inc

Inventors

• Gentry Timothy
• Reynolds Bruce David
• Nolcheff Nick

Classifications

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F01D5/20

  Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)} · CPC title

• F04D29/324

  Blades · CPC title

• F04D29/685 Primary

  Inducing localised fluid recirculation in the stator-rotor interface · CPC title

• F04D29/526 Primary

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