Diffuser pipe with exit flare

Patent metadata

Field	Value
Publication number	US-11859543-B2
Application number	US-202217967501-A
Country	US
Kind code	B2
Filing date	Oct 17, 2022
Priority date	Jun 3, 2019
Publication date	Jan 2, 2024
Grant date	Jan 2, 2024

Abstract

A diffuser pipe has a tubular body defining a pipe center axis extending therethrough. The tubular body includes a first portion extending in a generally radial direction from an inlet of the tubular body, a second portion extending in a generally axial direction and terminating at a pipe outlet, and a bend portion fluidly linking the first portion and the second portion. The tubular body has a length defined between the inlet and the pipe outlet. The tubular body has cross-sectional profiles defined in a plane normal to the pipe center axis. An area of the cross-sectional profile at the pipe outlet is at least 20% greater than an area of the cross-sectional profile at a point upstream from the pipe outlet a distance corresponding to 10% of the length of the tubular body.

First claim

The invention claimed is:

1. 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 at a first rate for about eighty percent (80%) of the length of the tubular body starting at the inlet end; and
wherein in a remaining about twenty percent (20%) of the length of the tubular body, the interior cross-sectional area of the tubular body increases by an amount equal to or greater than about thirty-three percent (33%) of said OEA.

2. The centrifugal compressor of claim 1 , wherein in the remaining about twenty percent (20%) of the length of the tubular body, the interior cross-sectional area of the tubular body increases by an amount of at least sixty percent (60%) of said OEA.

3. The centrifugal compressor of claim 2 , wherein in a ten percent (10%) of the length of the tubular body extending from the outlet end toward the inlet end, the interior cross-sectional area of the tubular body increases by an amount of about fifty percent (50%) of said OEA.

4. The centrifugal compressor of claim 1 , wherein in a ten percent (10%) of the length of the tubular body extending from the outlet end toward the inlet end, the interior cross-sectional area of the tubular body increases linearly at a second rate greater than the first rate.

5. The centrifugal compressor of claim 4 , wherein in the ten percent (10%) of the length of the tubular body extending from the outlet end toward the inlet end, the interior cross-sectional area of the tubular body increases by an amount of about fifty percent (50%) of said OEA.

6. The centrifugal compressor of claim 1 , wherein the interior cross-sectional area of the tubular body separated from the inlet end in a direction toward the outlet end by a distance that is equal to about eighty percent (80%) of the length of the tubular body, the interior cross-sectional area of the tubular body is equal to or less than forty percent (40%) of said OEA.

7. The centrifugal compressor of claim 1 , wherein the interior cross-sectional area of the tubular body separated from the inlet end in a direction toward the outlet end by a distance that is equal to about ninety percent (90%) of the length of the tubular body, the interior cross-sectional area of the tubular body is equal to or less than fifty percent (50%) of said OEA.

8. A gas turbine engine having a center axis, comprising:
a combustor section; and
a centrifugal compressor having an impeller configured for rotation the center axis, and 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 at a first rate for about eighty percent (80%) of the length of the tubular body starting at the inlet end; and
wherein in a remaining about twenty percent (20%) of the length of the tubular body, the interior cross-sectional area of the tubular body increases by an amount equal to or greater than about thirty-three percent (33%) of said OEA;
wherein the second portion of each of the plurality of diffuser pipes is oriented to direct the fluid flow axially into the combustor section.

9. The gas turbine engine of claim 8 , wherein in the remaining about twenty percent (20%) of the length of the tubular body, the interior cross-sectional area of the tubular body increases by an amount of at least sixty percent (60%) of said OEA.

10. The gas turbine engine of claim 9 , wherein in a ten percent (10%) of the length of the tubular body extending from the outlet end toward the inlet end, the interior cross-sectional area of the tubular body increases by an amount of about fifty percent (50%) of said OEA.

11. The gas turbine engine of claim 8 , wherein in a ten percent (10%) of the length of the tubular body extending from the outlet end toward the inlet end, the interior cross-sectional area of the tubular body increases linearly at a second rate greater than the first rate.

12. The gas turbine engine of claim 11 , wherein in the ten percent (10%) of the length of the tubular body extending from the outlet end toward the inlet end, the interior cross-sectional area of the tubular body increases by an amount of about fifty percent (50%) of said OEA.

13. The gas turbine engine of claim 8 , wherein the interior cross-sectional area of the tubular body separated from the inlet end in a direction toward the outlet end by a distance that is equal to about eighty percent (80%) of the length of the tubular body, the interior cross-sectional area of the tubular body is equal to or less than forty percent (40%) of said OEA.

14. The gas turbine engine of claim 8 , wherein the interior cross-sectional area of the tubular body separated from the inlet end in a direction toward the outlet end by a distance that is equal to about ninety percent (90%) of the length of the tubular body, the interior cross-sectional area of the tubular body is equal to or less than fifty percent (50%) of said OEA.

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 i

Assignees

• Pratt & Whitney Canada

Inventors

• Nichols Jason
• Perera Ryan

Classifications

• F02C6/06 Primary

  providing compressed gas (F02C6/10 takes precedence) · CPC title

• F02C7/32

  Arrangement, mounting, or driving, of auxiliaries · CPC title

• F02K3/00

  Plants including a gas turbine driving a compressor or a ducted fan · CPC title

• F04D29/284

  for compressors · CPC title

• F04D29/288

  Part of the wheel having an ejecting effect, e.g. being bladeless diffuser · CPC title