Diffuser pipe with axially-directed exit
AssigneePratt & Whitney Canada Corp.
InventorHien DUONG
Life of this patent
Estimating the term…
Abstract
A compressor diffuser for a gas turbine engine includes diffuser pipes having a tubular body including a generally radial portion, a bend portion and a generally axial portion. The generally axial portion has an exit segment extending parallel to the center axis and terminating at a pipe outlet. The bend portion is disposed radially further from the center axis than the exit segment.
Claims19
A compressor diffuser for a gas turbine engine having a center axis, the compressor diffuser comprising:
- diffuser pipes having a tubular body including a generally radial portion, a bend portion and a generally axial portion, the generally axial portion having an exit segment extending parallel to the center axis and terminating at a pipe outlet, the bend portion disposed radially further from the center axis than the exit segment.
A gas turbine engine, comprising:
- a compressor having an impeller rotatable about a center axis, and having a radial impeller outlet;
- a diffuser with diffuser pipes to receive fluid from the radial impeller outlet, and having a tubular body including a generally radial portion, a bend portion and a generally axial portion, the generally axial portion having an exit segment extending parallel to the center axis and terminating at a pipe outlet, the bend portion disposed radially further from the center axis than the exit segment;
- and
- a reverse-flow combustor downstream of the diffuser.
A method of modifying a vibratory response of a diffuser pipe of a compressor with a center axis, the method comprising:
- positioning a bend portion of the diffuser pipe radially outwardly from the center axis and from an outlet of the diffuser pipe, and orienting an exit segment of the diffuser pipe to be parallel with the center axis.
Dependencies are inferred from the claim text.