Gas turbine engine with dove-tailed tobi vane

Patent metadata

Field	Value
Publication number	US-2016108748-A1
Application number	US-201414892138-A
Country	US
Kind code	A1
Filing date	May 28, 2014
Priority date	Jun 4, 2013
Publication date	Apr 21, 2016
Grant date	—

Abstract

A combustor assembly for a gas turbine engine includes a TOBI module which includes a TOBI housing. The TOBI housing has a slot. A vane including a dovetail is removably received within the slot.

First claim

What is claimed is:

1 . A combustor assembly for a gas turbine engine comprising:
a TOBI module including a TOBI housing, the TOBI housing having a slot; and a vane including a dovetail removably received within the slot.

2 . The combustor assembly according to claim 1 , wherein the TOBI housing includes an axially extending TOBI nozzle array.

3 . The combustor assembly according to claim 2 , wherein the TOBI housing includes a plenum, and a cooling passage fluidly connects the plenum to the vane.

4 . The combustor assembly according to claim 3 , wherein the TOBI housing includes passages configured to provide cooling fluid to the vane.

5 . The combustor assembly according to claim 4 , wherein the TOBI housing includes a first passageway further connecting the TOBI nozzle to the plenum.

6 . The combustor assembly according to claim 5 , wherein the TOBI housing includes a second passage configured to fluidly connect a cavity external to the TOBI nozzle to the plenum.

7 . The combustor assembly according to claim 3 , wherein the TOBI housing includes an access hole fluidly connected to the plenum and configured to provide access to a fastener on an opposite side of the plenum from the access hole.

8 . The combustor assembly according to claim 1 , comprising a diffuser case secured to the TOBI housing.

9 . The combustor assembly according to claim 1 , wherein the TOBI housing includes a stop adjacent to the slot, the stop providing an aftmost position of the vane with respect to the TOBI housing.

10 . The combustor assembly according to claim 1 , wherein the dovetail includes an edge abutting at least one of the diffuser case and a combustor housing.

11 . The combustor assembly according to claim 10 , comprising a combustor housing secured to the diffuser case and TOBI housing.

12 . The combustor assembly according to claim 1 , wherein the vane includes a platform supporting a radially extending airfoil and providing an inner flow path surface, and the dovetail is mounted to the platform.

13 . A gas turbine engine comprising:
a combustor section including a combustor assembly; a turbine section having a first fixed stage; and wherein the combustor assembly includes a TOBI module having a TOBI housing, the TOBI housing having a slot, and an array of vanes providing the first fixed stage and including a dovetail removably received within the slot.

14 . The gas turbine engine according to claim 13 , wherein the TOBI housing includes an axially extending TOBI nozzle array and a plenum, and a cooling passage fluidly connects the plenum to the vane, and the TOBI housing includes passages configured to provide cooling fluid to the vane.

15 . The gas turbine engine according to claim 13 , wherein the combustor assembly includes a combustor housing and a diffuser case secured to the TOBI housing.

16 . A fixed stage of a gas turbine engine comprising:
an annular structured fixed to an engine static structure and including multiple circumferentially arranged axially extending slots; and an array of vanes removable mounted in the slots, the vanes including airfoils extending radially outward from the slots.

17 . The fixed stage according to claim 16 , wherein the annular structure provides a TOBI housing having an axially extending TOBI nozzle array.

18 . The fixed stage according to claim 17 , wherein a combustor housing and a diffuser case are secured to the TOBI housing.

19 . The fixed stage according to claim 17 , wherein the TOBI housing includes a plenum, and a cooling passage fluidly connects the plenum to the vane, and the TOBI housing includes passages configured to provide cooling fluid to the vane.

20 . The fixed stage according to claim 16 , wherein outer ends of the vanes are secured relative to the engine static structure.

Assignees

• United Technologies Corp

Inventors

• Harris Meggan

Classifications

• F01D5/081

  Cooling fluid being directed on the side of the rotor disc or at the roots of the blades (F01D5/087 takes precedence) · CPC title

• F01D25/12

  Cooling · CPC title

• F01D9/042 Primary

  fixing blades to stators (fixing stator-rings in the casing or to each other F01D25/246) · CPC title

• F01D5/3007

  of axial insertion type · CPC title

• F05D2220/3212

  the first stage of a turbine · CPC title