Shaft assembly of a gas turbine engine and method of controlling flow therein

Patent metadata

Field	Value
Publication number	US-9803550-B2
Application number	US-201414230789-A
Country	US
Kind code	B2
Filing date	Mar 31, 2014
Priority date	Mar 31, 2014
Publication date	Oct 31, 2017
Grant date	Oct 31, 2017

Abstract

A gas turbine engine comprises a shaft assembly including a hollow shaft of the gas turbine engine and a plug connected to the inlet end of the shaft. The hollow shaft has a shaft bore having a bore diameter. The hollow shaft has an inlet end for receiving a first portion of an incoming air flow. The plug has a plug bore therethrough, and an inlet end having an inlet diameter. The inlet diameter of the plug is smaller than the bore diameter. The plug includes a deflection surface adapted to deflect a second portion of the incoming air flow away from the shaft bore. A plug for connecting to an end of a hollow shaft of a gas turbine engine and s method of controlling a flow of fluid through a shaft having a bore therethrough of a gas turbine engine are also presented.

First claim

The invention claimed is:

1. A gas turbine engine comprising:
a shaft assembly comprising:
a hollow shaft of the gas turbine engine, the hollow shaft having a shaft bore having a bore diameter, the hollow shaft having an inlet end for receiving a first portion of an incoming air flow; and
a plug connected to the inlet end of the shaft, the plug having a plug bore therethrough, the plug having an inlet end having an inlet diameter, the inlet diameter of the plug being smaller than the bore diameter, the plug including a deflection surface adapted to deflect a second portion of the incoming air flow away from the shaft bore.

2. The gas turbine engine as defined in claim 1 , wherein the deflection surface is on an outer surface of the plug and faces away from the shaft in order to deflect a second portion of the incoming air flow away from the shaft bore.

3. The gas turbine engine as defined in claim 1 , wherein the plug is threaded to one of an inside and an outside of the inlet end of the shaft.

4. The gas turbine engine as defined in claim 1 , wherein the inlet end of the plug extends upstream of the shaft.

5. The gas turbine engine as defined in claim 3 , wherein the deflection surface of the plug is flaring outwardly from the inlet end toward the shaft.

6. The gas turbine engine as defined in claim 1 , wherein the plug further comprises a grasping portion disposed between the shaft and the deflection surface of the plug.

7. The gas turbine engine as defined in claim 6 , wherein the grasping portion is hexagonal in cross-section.

8. The gas turbine engine as defined in claim 1 , wherein the plug bore includes a fairing portion extending from the inlet end of the plug toward the shaft.

9. The gas turbine engine as defined in claim 1 , wherein the plug is a power turbine plug and the shaft is a power turbine shaft.

10. The gas turbine engine as defined in claim 1 , wherein the inner diameter of the plug at the inlet end corresponds to a diameter providing a minimum flow rate of incoming fluid to the shaft bore for cooling the shaft.

11. The gas turbine engine as defined in claim 1 , wherein the plug bore is coaxial with the shaft bore.

12. A method of controlling a flow of fluid through a hollow shaft having a bore therethrough of a gas turbine engine, the method comprising:
allowing a first portion of an incoming flow through an inlet of a hollow plug connected to the shaft, the inlet having a diameter smaller than a diameter of the bore of the hollow shaft; and
directing a second portion of the incoming flow away from the shaft via a deflection surface of the plug.

13. The method as defined in claim 12 , wherein directing the second portion of the incoming flow via the deflection surface of the plug comprises directing the second portion of the incoming flow via the deflection surface flaring outwardly from the inlet of the plug.

14. The method as defined in claim 12 , wherein allowing the first portion of the incoming flow through the inlet of the hollow plug includes allowing a majority of the incoming flow through the inlet of the hollow plug.

Assignees

• Pratt & Whitney Canada

Inventors

• Paradis Vincent
• Synnott Rémy

Classifications

• F02C9/18

  by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} · CPC title

• F01D5/085

  cooling fluid circulating inside the rotor · CPC title

• F02C7/18 Primary

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F15D1/025

  by means of orifice or throttle elements · CPC title