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US 2010/0166552 A1Published application
Diffuser for a compressor
AssigneeRolls-Royce North American Technologies Inc.
InventorCalvin W. Emmerson
Life of this patent
Estimating the term…
Abstract
A diffuser is provided having a number of diffuser channels defined by a top wall, bottom wall, and two sidewalls. The sidewalls can be constructed according to an involute of a circle which provides constant interwall distance between the sidewalls along the length of the diffuser channel. The top and bottom walls, however, diverge from one another along the length of the diffuser channel to provide a desired diffusion.
Claims26
A gas turbine engine apparatus comprising:
- a diffuser structured to receive a working fluid from a gas turbine engine centrifugal compressor, the diffuser having two sidewalls, each of the two sidewalls at least partially defined by an involute of a circle, wherein an interwall distance between the two sidewalls is substantially constant over at least a portion of the length of the two sidewalls.
An apparatus comprising:
- a gas turbine engine compressor diffuser channel defined by a set of walls having a height and an interwall distance, wherein the height increases along the length of the gas turbine engine compressor diffuser channel and wherein a fluid diffusion caused by the height is greater than a fluid diffusion caused by the interwall distance.
An apparatus comprising:
- a gas turbine diffuser channel having an axial diffusion and a circumferential diffusion, wherein the axial diffusion provides a greater diffusion than the circumferential diffusion.
A method comprising:
- constructing a gas turbine engine diffuser wall at least partially defined by an involute of a circle.
Dependencies are inferred from the claim text.