Variable span splitter blade

Patent metadata

Field	Value
Publication number	US-9976422-B2
Application number	US-201314768964-A
Country	US
Kind code	B2
Filing date	Dec 31, 2013
Priority date	Feb 26, 2013
Publication date	May 22, 2018
Grant date	May 22, 2018

Abstract

The presently disclosed embodiments utilize flow from a higher-energy portion of flow within the impeller flow path and inject it into the lower-energy portion of the flow path to re-energize the flow, delaying the onset of, or minimizing, large (and inefficient, entropy-generating) re-circulation zones in the flow field. By making a spanwise cut along the chord length of the splitter blade (variable blade clearance from leading edge to trailing edge), additional secondary flow occurs within the flow passages as the higher pressure flow on the pressure side of the blade can now spill over into the low-pressure suction side of the blade.

First claim

What is claimed:

1. A compressor for a gas turbine engine, the compressor comprising:
a flow passage shroud;
a flow passage hub;
main blades; and
a splitter blade disposed adjacent the flow passage shroud, wherein the splitter blade includes a leading edge, a trailing edge, and a chord length;
wherein a clearance between the splitter blade and the flow passage shroud is variable along the chord length of the splitter blade;
wherein the clearance at the leading edge is between approximately 10% and <100% of a first span between the flow passage hub and the flow passage shroud at the leading edge; and

wherein the clearance at the trailing edge is approximately less than 1.5% of a second span between the flow passage hub and the flow passage shroud at the trailing edge.

2. The compressor of claim 1 , wherein the clearance between the splitter blade and the flow passage shroud along the chord length of the splitter blade varies linearly.

3. The compressor of claim 1 , wherein the clearance between the splitter blade and the flow passage shroud along the chord length of the splitter blade varies nonlinearly.

4. The compressor of claim 1 , wherein the clearance between the splitter blade and the flow passage shroud along the chord length of the splitter blade varies linearly in at least one segment and nonlinearly in at least another segment.

5. The compressor of claim 1 , wherein the clearance at the leading edge is approximately 50% of the first span between the flow passage hub and the flow passage shroud at the leading edge; and wherein the clearance at the trailing edge is approximately less than 1.5% of the second span between the flow passage hub and the flow passage shroud at the trailing edge.

6. A gas turbine engine, comprising the compressor of claim 1 .

7. The gas turbine engine of claim 6 , wherein the clearance between the splitter blade and the flow passage shroud along the chord length of the splitter blade varies linearly.

8. The gas turbine engine of claim 6 , wherein the clearance between the splitter blade and the flow passage shroud along the chord length of the splitter blade varies nonlinearly.

9. The gas turbine engine of claim 6 , wherein the clearance between the splitter blade and the flow passage shroud along the chord length of the splitter blade varies linearly in at least one segment and nonlinearly in at least another segment.

10. The gas turbine engine of claim 6 , wherein: the clearance at the leading edge is approximately 50% of the first span between the flow passage hub and the flow passage shroud at the leading edge; and the clearance at the trailing edge is approximately less than 1.5% of the second span between the flow passage hub and the flow passage shroud at the trailing edge.

11. A compressor for a gas turbine engine, the compressor comprising:
a flow passage shroud;
a flow passage hub;
main blades; and
a splitter blade disposed adjacent the flow passage shroud, wherein the splitter blade includes a leading edge, a trailing edge, and a chord length;
wherein a clearance between the splitter blade and the flow passage shroud is variable along the chord length of the splitter blade;
wherein the clearance at the leading edge is approximately less than 1.5% of a first span between the flow passage hub and the flow passage shroud at the leading edge; and wherein the clearance at the trailing edge is between approximately 10% and <100% of a second span between the flow passage hub and the flow passage shroud at the trailing edge.

12. A gas turbine engine, comprising the compressor of claim 11 .

13. A compressor for a gas turbine engine, the compressor comprising:
a flow passage shroud;
a flow passage hub;
main blades; and
a splitter blade disposed adjacent the flow passage shroud, wherein the splitter blade includes a leading edge, a trailing edge, and a chord length;
wherein a clearance between the splitter blade and the flow passage shroud is variable along the chord length of the splitter blade;
wherein the clearance at the leading edge is between approximately 10% and <100% of a first span between the flow passage hub and the flow passage shroud at the leading edge; and wherein the clearance at the trailing edge is between approximately 10% and <100% of a second span between the flow passage hub and the flow passage shroud at the trailing edge.

14. A gas turbine engine, comprising the compressor of claim 13 .

Assignees

• United Technologies Corp

Inventors

• Fishler Benjamin E

Classifications

• F04D29/681

  especially adapted for elastic fluid pumps · CPC title

• F04D29/30

  Vanes · CPC title

• F01D5/02

  Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) · CPC title

• F04D29/284

  for compressors · CPC title

• F05D2250/90

  Variable geometry · CPC title