Flexible flange design
AssigneeRtx Corporation
InventorsPedro Rivero, William Blickenstaff, III, Peter Milligan, Angela Reisch
Life of this patent
Estimating the term…
Abstract
An annular flexible flange is provided for connecting components of a gas turbine engine having different rates of thermal response to transient thermal events. The annular flexible flange is disposed about an axis and extends radially from an annular body. The annular flexible flange includes a plurality of fastener flanges spaced circumferentially about the flexible flange and a plurality of flexible arms connected to the annular body and connected to the plurality of fastener flanges. The plurality of flexible arms are configured to flex in a radial direction. The plurality of fastener flanges are separated from the annular body by a gap.
Claims16
An annular flexible flange for connecting components of a gas turbine engine having different rates of thermal response to transient thermal events, the annular flexible flange disposed about an axis and extending radially from an annular body, the annular flexible flange comprising:
- a plurality of fastener flanges spaced circumferentially about the flexible flange, wherein each of the plurality of fastener flanges is separated from the annular body by a respective radial gap;
- and
- a plurality of flexible arms configured to flex in a radial direction, the plurality of flexible arms extending in a circumferential direction between adjacent fastener flanges of the plurality of fastener flanges, the plurality of flexible arms each having a first end connected to the annular body and a second end connected to a corresponding one of the plurality of fastener flanges,
- wherein each of the plurality of fastener flanges is disposed between and connected to adjacent ones of the plurality of flexible arms, each of the plurality of fastener flanges having a first circumferential end connected to the second end of a first of the respective adjacent flexible arms, and each of the plurality of fastener flanges having a second circumferential end connected to the second end of a second of the respective adjacent flexible arms, and
- wherein each of the plurality of flexible arms has an axial thickness and a radial height, wherein the axial thickness is greater than the radial height.
An inner combustor shell of a gas turbine engine, the inner combustor shell configured to be connected to a component having a comparatively slower thermal response to a transient thermal event, the inner combustor shell disposed about an axis and comprising:
- an annular body defining at least a portion of a combustion chamber;
- and
- an annular flexible flange extending radially from the annular body, the annular flexible flange comprising:
- a plurality of fastener flanges spaced circumferentially about the flexible flange, wherein each of the plurality of fastener flanges is separated from the annular body by a respective radial gap;
- and
- a plurality of flexible arms configured to flex in a radial direction, each of the plurality of flexible arms extending in a circumferential direction between adjacent ones of the plurality of fastener flanges, each of the plurality of flexible arms having a first end connected to the annular body and a second end connected to a corresponding one of the plurality of fastener flanges;
- wherein each of the plurality of fastener flanges is disposed between and connected to adjacent ones of the plurality of flexible arms, with each of the plurality of fastener flanges having a first circumferential end connected to the second end of a first of the respective adjacent flexible arms, and each of the plurality of fastener flanges having a second circumferential end connected to the second end of a second of the respective adjacent flexible arms, and
- wherein each of the plurality of flexible arms has an axial thickness and a radial height, wherein the axial thickness is greater than the radial height.
Dependencies are inferred from the claim text.