Tie shaft flow trip

Patent metadata

Field	Value
Publication number	US-9670780-B2
Application number	US-201414774196-A
Country	US
Kind code	B2
Filing date	Feb 18, 2014
Priority date	Mar 11, 2013
Publication date	Jun 6, 2017
Grant date	Jun 6, 2017

Abstract

A compressor section includes, among other things, a tie shaft assembly including a shaft and one or more projections extending radially outward from the shaft. The projections are configured to redirect air communicated from between the one or more rotor stages and the shaft.

First claim

I claim:

1. A compressor section, comprising:
one or more rotor stages;
a tie shaft assembly including a shaft; and
one or more projections extending radially outward from the shaft, the projections configured to redirect air communicated from between the one or more rotor stages and the shaft, wherein at least one of the projections has a peak and a leading edge, the peak positioned directly aft one of the rotor stages, the leading edge positioned under the one of the rotor stages.

2. The compressor section of claim 1 , wherein the one or more rotor stages are integrally bladed rotors.

3. The compressor section of claim 1 , wherein the projections have a base section and a peak section, and wherein the base section has an axial width greater than an axial width of the peak section.

4. The compressor section of claim 1 , wherein the one or more projections extend radially from the shaft for a distance less than the distance between the one or more rotor stages and the shaft.

5. The compressor section of claim 1 , wherein the diameter of the shaft is 5 inches (127 mm) and the one or more projections extend radially from the shaft for a distance of 0.2 inches (5.08 mm).

6. The compressor section of claim 1 , wherein the one or more projections are machined into the tie shaft.

7. The compressor section of claim 1 , wherein the one or more projections are configured to direct air radially away from the shaft.

8. A gas turbine engine, comprising:
a compressor section including a tie shaft and one or more rotor stages arranged on the tie shaft, wherein the tie shaft includes one or more projections extending radially outward from the tie shaft and configured to direct air communicated from between the one or more rotor stages and the tie shaft to one or more spaces between the one or more rotor stages, wherein at least one of the projections has a peak and a leading edge, the peak positioned directly aft one of the rotor stages, the leading edge positioned under the one of the rotor stages.

9. The gas turbine engine of claim 8 , wherein the rotor stages are integrally bladed rotors.

10. The gas turbine engine of claim 8 , wherein the one or more projections have a base section and a peak section, and wherein the base section has an axial width greater than an axial width of the peak section.

11. The gas turbine engine of claim 8 , wherein the one or more projections extend radially from the tie shaft for a distance less than the distance between the one or more rotor stages and the tie shaft.

12. The gas turbine engine of claim 8 , wherein the diameter of the tie shaft is 5 inches (127 mm) and the one or more projections extend radially from the tie shaft for a distance of 0.2 inches (5.08 mm).

13. The compressor section of claim 8 , wherein the one or more projections are configured to direct air radially away from the tie shaft.

14. A method of cooling a compressor section, comprising:
providing one or more rotor stages arranged on a tie shaft; and
providing one or more projections extending radially outward from the tie shaft to direct air between one or more rotor stages, wherein at least one of the projections has a peak and a leading edge, the peak positioned directly aft one of the rotor stages, the leading edge positioned under the one of the rotor stages.

Assignees

• United Technologies Corp

Inventors

• Baxley Richard C

Classifications

• F05D2240/60

  Shafts · CPC title

• F05D2250/232

  conical · CPC title

• F01D5/085

  cooling fluid circulating inside the rotor · CPC title

• F01D25/12

  Cooling · CPC title

• F05D2250/11

  triangular · CPC title