Vane support system

Patent metadata

Field	Value
Publication number	US-12359622-B2
Application number	US-202016844596-A
Country	US
Kind code	B2
Filing date	Apr 9, 2020
Priority date	Apr 9, 2020
Publication date	Jul 15, 2025
Grant date	Jul 15, 2025

Abstract

A gas turbine engine support system includes a support arc segment piece that defines radially inner and outer sides, axially forward and aft sides, and first and second circumferential mate face sides. The radially inner side has a radially open socket that is configured to engage a mating component and transmit loads from the mating component. The radially open socket is elongated in an axial direction with respect to the axially forward and aft sides The support arc segment piece has radial and axial reaction surfaces that are configured, respectively, to transmit radial and axial components of the loads from the mating component.

First claim

What is claimed is:

1. A gas turbine engine support system comprising:
a support arc segment piece defining a first radial side and a second radial side, an axially forward side that is forward-facing and an axially aft side that is aft-facing, and a first circumferential mate face side and a second circumferential mate face side, the first radial side having a radially open socket configured to engage a mating component and transmit loads from the mating component, the radially open socket being elongated in an axial direction with respect to the axially forward side and the axially aft side and the radially open socket defining a length along which the radially open socket is curved, the support arc segment piece having a radial reaction surface and an axial reaction surface configured, respectively, to transmit radial and axial components of the loads from the mating component.

2. The gas turbine engine support system as recited in claim 1 , wherein the support arc segment piece is a single crystal alloy.

3. The gas turbine engine support system as recited in claim 1 , wherein the radially open socket extends from the axially forward side to the axially aft side.

4. The gas turbine engine support system as recited in claim 1 , wherein the radial reaction surface extends from the first circumferential mate face side to the second circumferential mate face side.

5. The gas turbine engine support system as recited in claim 4 , wherein the axial reaction surface extends from the first circumferential mate face side to the second circumferential mate face side.

6. The gas turbine engine support system as recited in claim 1 , wherein the first radial side includes a seal slot that has a first portion and a second portion, the first portion of the seal slot is between the first circumferential mate face side and the radially open socket and the second portion of the seal slot is between the second circumferential mate face side and the radially open socket.

7. The gas turbine engine support system as recited in claim 6 , wherein each of the seal slot include an axial leg and a circumferential leg.

8. The gas turbine engine support system as recited in claim 1 , wherein the second radial side has an anti-rotation lock.

9. The gas turbine engine support system as recited in claim 1 , wherein the support arc segment piece defines a manifold region and at least one opening that connects the second radial side with the manifold region.

10. A gas turbine engine support system comprising:
an outer case;
vane support arc segment pieces, each said vane support arc segment piece defining a first radial side and a second radial side, an axially forward side that is forward-facing and an axially aft side that is aft-facing, and a first circumferential mate face side and a second circumferential mate face side, the first radial side having a radially open socket, the radially open socket being elongated in an axial direction with respect to the axially forward side and the axially aft side, the vane support arc segment piece having a radial reaction surface and an axial reaction surface on, respectively, the second radial side and the axially aft side, the a radial reaction surface and the axial reaction surface interfacing with the outer case; and
vane arc segments, each said vane arc segment defining a platform and an airfoil section extending from the platform, the platform defining a radial flange of complementary geometry to the radially open sockets of the vane support arc segment pieces, the radial flange projecting into a corresponding one of the radially open sockets to transmit loads through the vane support arc segment piece to the outer case via the a radial reaction surface and the axial reaction surface.

11. The gas turbine engine support system as recited in claim 10 , wherein the vane support arc segment piece is a single crystal alloy and the vane arc segments are formed of ceramic matrix composite.

12. The gas turbine engine support system as recited in claim 11 , wherein the first radial side includes a seal slot that has a first portion and a second portion, the first portion of the seal slot is between the first circumferential mate face side and the radially open socket and the second portion of the seal slot is between the second circumferential mate face side and the radially open socket.

13. The gas turbine engine support system as recited in claim 12 , wherein the seal slot includes an axial leg and a circumferential leg.

14. The gas turbine engine support system as recited in claim 13 , wherein the axial and radial reaction surfaces extend from the first circumferential mate face side to the second circumferential mate face side.

15. The gas turbine engine support system as recited in claim 14 , wherein the second radial side has an anti-rotation lock, and the vane support arc segment piece defines a manifold region and at least one opening that connects the radially outer side with the manifold region.

16. The gas turbine engine support system as recited in claim 15 , wherein the radially open socket extends from the axially forward side to the axially aft side and defines a length along which the radially open socket is curved.

17. A gas turbine engine vane support system comprising:
an outer case;
vane support arc segment pieces, each said vane support arc segment piece defining a first radial side and a second radial side, an axially forward side that is forward-facing and an axially aft side that is aft-facing, and a first circumferential mate face side and a second circumferential mate face side, the first radial side having a radially open socket, the radially open socket being elongated in an axial direction with respect to the axially forward side and the axially aft side, the vane support arc segment piece having a radial reaction surface and an axial reaction surface on, respectively, the second radial side and the axially aft side, the a radial reaction surface and the axial reaction surface interfacing with the outer case;
vane arc segments, each said vane arc segment defining a platform and an airfoil section extending from the platform, the platform defining a radial flange of complementary geometry to the radially open sockets of the vane support arc segment pieces, the radial flange projecting into a corresponding one of the radially open sockets and transmitting aerodynamic loads from the vane arc segment through the vane support arc segment piece to the outer case via a radial reaction surface and the axial reaction surface.

18. The gas turbine engine support system as recited in claim 17 , wherein the vane support arc segment piece is a single crystal alloy and the vane arc segments are formed of ceramic matrix composite.

Assignees

• United Technologies Corp
• Rtx Corp

Inventors

• Sobanski Jon E
• Liles Howard J

Classifications

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F05D2240/11

  Shroud seal segments · CPC title

• F01D9/042 Primary

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

• F05D2240/80

  Platforms for stationary or moving blades · CPC title

• F01D9/065

  Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26) · CPC title