Radial inlet compressor

Patent metadata

Field	Value
Publication number	US-12577909-B2
Application number	US-202418815308-A
Country	US
Kind code	B2
Filing date	Aug 26, 2024
Priority date	Aug 26, 2024
Publication date	Mar 17, 2026
Grant date	Mar 17, 2026

Abstract

A radial inlet body of a gas turbine engine compressor is provided. The radial inlet body includes plenums arranged around opposite sides of an inlet portion defining a compressor inlet. The plenums include outer surfaces with increasing radii of curvature and a flow diverter. The flow diverter is disposed aside the inlet portion opposite a duct. The plenums are configured to direct flows from the duct around the inlet portion. The flow diverter and the plenums are configured to cooperatively encourage uniform distribution of the flows. The flow diverter includes curvilinear sides that tangentially register with and smoothly lead to the outer surfaces of the plenums and a cusp where the curvilinear sides meet. The radial inlet body further includes a front sidewall supporting the inlet portion and an aft sidewall opposite the front sidewall. The front and aft sidewalls are angled toward one another along the plenums.

First claim

What is claimed is:

1 . A radial inlet body of a gas turbine engine compressor, the radial inlet body comprising:
a flow diverter; plenums arranged around opposite sides of an inlet portion defining a compressor inlet, the plenums comprising outer surfaces with increasing radii of curvature exhibiting increasing distance from the inlet portion and decreasing distance to the flow diverter, the flow diverter being disposed aside the inlet portion opposite a duct, the plenums being configured to direct flows from the duct around the inlet portion, the flow diverter and the plenums being configured to cooperatively encourage uniform distribution of the flows and the flow diverter comprising:
curvilinear sides that tangentially register with and smoothly lead to the outer surfaces of the plenums; and
a cusp where the curvilinear sides meet; and
a front sidewall supporting the inlet portion and an aft sidewall opposite the front sidewall, the front and aft sidewalls being angled toward one another along the plenums.

2 . The radial inlet body according to claim 1 , wherein the outer surfaces are parabolic.

3 . The radial inlet body according to claim 1 , wherein the plenums comprise the outer surfaces with the increasing radii of curvature from a midpoint of the inlet portion to the flow diverter.

4 . The radial inlet body according to claim 1 , wherein the flow diverter is aligned with a center line of the duct and the plenums and the flow diverter are symmetric about the center line.

5 . The radial inlet body according to claim 1 , wherein the flow diverter is offset from a center line of the duct and the plenums and the flow diverter are asymmetric.

6 . The radial inlet body according to claim 1 , wherein the aft sidewall is entirely flat and the front sidewall comprises an angled portion which is angled toward the aft sidewall.

7 . The radial inlet body according to claim 1 , wherein the front and aft sidewalls each comprise an angled portion angled toward the opposite angled portion.

8 . A radial inlet of a gas turbine engine compressor, the radial inlet comprising:
an inlet portion defining a compressor inlet; a duct; and a body, comprising:
a flow diverter;
plenums arranged around opposite sides of the inlet portion, the plenums comprising outer surfaces with increasing radii of curvature exhibiting increasing distance from the inlet portion and decreasing distance to the flow diverter,
the flow diverter being disposed aside the inlet portion opposite the duct, the plenums being configured to direct flows from the duct around the inlet portion, the flow diverter and the plenums being configured to cooperatively encourage uniform distribution of the flows and the flow diverter comprising:
curvilinear sides that tangentially register with and smoothly lead to the outer surfaces of the plenums; and
a cusp where the curvilinear sides meet; and

a front sidewall supporting the inlet portion and an aft sidewall opposite the front sidewall, the front and aft sidewalls being angled toward one another along the plenums.

9 . The radial inlet according to claim 8 , wherein the outer surfaces are parabolic.

10 . The radial inlet according to claim 8 , wherein the plenums comprise the outer surfaces with the increasing radii of curvature from a midpoint of the inlet portion to the flow diverter.

11 . The radial inlet according to claim 8 , wherein the flow diverter is aligned with a center line of the duct and the plenums and the flow diverter are symmetric about the center line.

12 . The radial inlet according to claim 8 , wherein the flow diverter is offset from a center line of the duct and the plenums and the flow diverter are asymmetric.

13 . The radial inlet according to claim 8 , wherein the aft sidewall is entirely flat and the front sidewall comprises an angled portion which is angled toward the aft sidewall.

14 . The radial inlet according to claim 8 , wherein the front and aft sidewalls each comprise an angled portion angled toward the opposite angled portion.

15 . A radial inlet of a gas turbine engine compressor, the radial inlet comprising:
an inlet portion defining a compressor inlet leading to a compressor section; a duct by which air is directed from an exterior toward the inlet portion; and a body, comprising:
a flow diverter;
plenums arranged around opposite sides of the inlet portion, the plenums comprising outer surfaces with increasing radii of curvature exhibiting increasing distance from the inlet portion and decreasing distance to the flow diverter,
the flow diverter being disposed aside the inlet portion opposite the duct, the plenums being configured to direct flows from the duct around the inlet portion, the flow diverter and the plenums being configured to cooperatively encourage uniform distribution of the flows and the flow diverter comprising:
curvilinear sides that tangentially register with and smoothly lead to the outer surfaces of the plenums; and
a cusp where the curvilinear sides meet; and

a front sidewall supporting the inlet portion and an aft sidewall opposite the front sidewall, the front and aft sidewalls being angled toward one another along the plenums.

16 . The radial inlet according to claim 15 , wherein the outer surfaces are parabolic.

17 . The radial inlet according to claim 15 , wherein the plenums comprise the outer surfaces with the increasing radii of curvature from a midpoint of the inlet portion to the flow diverter.

18 . The radial inlet according to claim 15 , wherein the flow diverter is aligned with a center line of the duct and the plenums and the flow diverter are symmetric about the center line.

19 . The radial inlet according to claim 15 , wherein the flow diverter is offset from a center line of the duct and the plenums and the flow diverter are asymmetric.

20 . The radial inlet according to claim 15 , wherein at least one of:
the aft sidewall is entirely flat and the front sidewall comprises an angled portion which is angled toward the aft sidewall, and the front and aft sidewalls each comprise an angled portion angled toward the opposite angled portion.

Assignees

• Pratt & Whitney Canada

Inventors

• O Brien James
• Cunningham Mark
• Yan Guorong

Classifications

• F04D29/4213

  suction ports · CPC title

• F02C3/08

  the compressor comprising at least one radial stage (F02C3/10 takes precedence) · CPC title

• F02C7/04 Primary

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title

• F05D2250/71

  curved · CPC title

• F05D2250/73

  asymmetric · CPC title