IP Library › Granted Patent US 11,092,025
Granted Patent B2
US 11,092,025 · App. 16/668,773 · Granted Aug 17, 2021

Gas turbine engine with dove-tailed TOBI vane

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Quick Facts
Patent No.
US 11,092,025
App. No.
16/668,773
Filed
Oct 30, 2019
Granted
Aug 17, 2021
Kind
B2
Art Unit
3745
USPC
415/177
Abstract

A combustor assembly for a gas turbine engine includes a TOBI module that includes a TOBI housing. The TOBI housing has a slot. A vane includes a dovetail removably received within the slot. The TOBI housing includes an axially extending TOBI nozzle array. The TOBI housing includes a plenum. A cooling passage fluidly connects the plenum to the vane. The TOBI housing includes passages configured to provide cooling fluid to the vane. The TOBI housing includes a first passageway further connecting the TOBI nozzle to the plenum.

Claims (24)

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, wherein the TOBI housing includes an axially extending TOBI nozzle array, the TOBI housing includes a plenum, and a cooling passage fluidly connects the plenum to the vane, the TOBI housing includes passages configured to provide cooling fluid to the vane, the TOBI housing includes a first passageway further connecting the TOBI nozzle to the plenum, wherein the cooling fluid flows from the TOBI nozzle, through the first passageway into the plenum, then from the plenum through the cooling passage into the vane.

2. The combustor assembly according to claim 1 , 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.

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

4. 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.

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

6. The combustor assembly according to claim 5 , comprising a combustor housing secured to the diffuser case and TOBI housing.

7. 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.

8. The combustor assembly according to claim 1 , wherein the TOBI housing is a unitary annular structure.

9. A combustor assembly for a gas turbine 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, wherein the TOBI housing includes an axially extending TOBI nozzle array, the TOBI housing includes a plenum, and a cooling passage fluidly connects the plenum to the vane, the TOBI housing includes passages configured to provide cooling fluid to the vane, the TOBI housing includes a first passageway further connecting the TOBI nozzle to the plenum, wherein the dovetail includes an edge abutting at least one of the diffuser case and a combustor housing, wherein the TOBI housing includes a second passage configured to fluidly connect a cavity external to the TOBI nozzle to the plenum.

10. 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;

an array of vanes, each of the vanes comprising a dovetail removably mounted in the slots, the vanes including airfoils extending radially outward from the slots; and

wherein the annular structure provides a TOBI housing having an axially extending TOBI nozzle array, 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, wherein the cooling fluid flows from the TOBI nozzle array, through a first passageway into the plenum, then from the plenum through the cooling passage into the vane.

11. The fixed stage according to claim 10 , wherein a combustor housing and a diffuser case are secured to the TOBI housing.

12. The fixed stage according to claim 11 , wherein the TOBI housing is a unitary annular structure.

13. The fixed stage according to claim 10 , wherein outer ends of the vanes are secured relative to the engine static structure.

14. The fixed stage according to claim 10 , wherein the TOBI housing includes passages configured to provide cooling fluid to the vane via the plenum.

15. The fixed stage according to claim 10 , wherein a nozzle of the TOBI nozzle array is fluidly connected to the plenum via a first passageway.

16. The fixed stage according to claim 10 , wherein the TOBI housing is configured to be secured to a combustor housing and a diffuser case.

17. The fixed stage according to claim 10 , 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.

18. The fixed stage according to claim 10 , 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.