Circumferentially self expanding combustor support for a turbine engine
AssigneeGeneral Electric Company
InventorRichard Martin DiCintio
Life of this patent
Estimating the term…
Abstract
A bullhorn or support for a turbine combustor is provided. The support maintains proper positioning of the transition element relative to the combustor while also allowing for certain movements of the support to alleviate mechanical stresses during turbine operation. The support is constructed from at least two pieces having an interlocking and releasable connection.
Claims17
A support assembly for positioning a transition segment to a combustor of a turbine engine, the combustor defining circumferential, axial and radial directions, the support assembly comprising:
- at least one pair of flanges mounted to the transition segment;
- and
- a support for mounting relative to the turbine engine, the support comprising at least one pair of arms mated together by an interlocking connection forming part of an elongated section of said support, the interlocking connection configured so as to fix the axial position of the at least one pair of arms relative to one another while allowing the at least one pair of arms to move along the radial and circumferential directions, the at least one pair of arms each extending along the radial direction, the at least one pair of arms terminating into a pair of fingers that extend along the axial direction and that are received by said flanges.
A support for securing a transition segment to a combustor of a turbine engine, the support comprising:
- a pair of arms releasably attached together by an interlocking connection, said pair of arms providing an elongated section defining the interlocking connection, said interlocking connection adapted so as to fix the axial movement of said arms relative to one another while allowing said arms to move along radial and circumferential directions of the turbine engine, said arms terminating into a pair of fingers that are connected to the transition segment and configured so as to allow the transition segment to move along the axial direction of the turbine engine.
Dependencies are inferred from the claim text.