Vane support system
AssigneeRtx Corporation
InventorsJon E. Sobanski, Howard J. Liles
Life of this patent
Estimating the term…
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.
Claims18
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.
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.
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.
Dependencies are inferred from the claim text.