Patent ID: 11859543
Assignee: PRATT & WHITNEY CANADA CORP.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 14:
15. A centrifugal compressor for a gas turbine engine, comprising:
an impeller configured for rotation about an axially extending axis of rotation;
a plurality of diffuser pipes positioned around an outer circumference of the impeller and configured to receive fluid flow exiting the impeller, each diffuser pipe including a tubular body having:
an open inlet end and an open outlet end;
a first portion, a second portion, and a bend portion, the first portion extending in a generally radial direction relative to the impeller axis of rotation between the inlet end and the bend portion, and the second portion extending in a generally axial direction between the outlet end and the bend portion;
a center axis that extends along a length of the tubular body between the inlet end and the outlet end;
wherein the tubular body has an interior cross-sectional area defined by a plane normal to the center axis, and the interior cross-sectional area at the outlet end is equal to an outlet end area (OEA); and
wherein the interior cross-sectional area of the tubular body increases linearly for about eighty percent (80%) of the length of the tubular body starting at the inlet end and the tubular body has a linear equivalent cone angle (ECA) from about ten percent (10%) of the length of the tubular body to about said eighty percent (80%) of the length of the tubular body, and has a said ECA greater than about six degrees from about ninety percent (90%) of the length of the tubular body to the outlet end of the tubular body.