Granted Patent B2

US 12,398,673 · App. 18/642,138 · Granted Aug 26, 2025

Inventors: Hien Duong (Mississauga, CA); Jason Nichols (Mississauga, CA)

Assignee: Pratt & Whitney Canada Corp.

F02C7/042F02C7/052F05D2260/607

Abstract

Claims (31)

1. An air intake plenum for a gas turbine engine, comprising:

an axial centerline;

a first gas path surface;

a second gas path surface, spaced apart from the first gas path surface, wherein the first gas path surface and the second gas path surface define at least a portion of a plenum interior configured for air passage; and

a plurality of struts that extend lengthwise between the first gas path surface and the second gas path surface through the plenum interior, each strut having a cross-section geometry within a plane perpendicular to a lengthwise axis of the strut, the cross-section geometry having a cross-section geometry center, a major axis, and a minor axis, where the major axis is greater than the minor axis, wherein the cross-section geometry is the same for each strut, and the cross-section geometry center disposed at an intersection of the major axis and the minor axis, and the cross-section is symmetrical about the cross-section geometry center;

wherein the plurality of struts are disposed circumferentially spaced apart from one another within the air intake plenum, and the plurality of struts are disposed circumferentially around the axial centerline;

wherein the plurality of struts includes a first strut, a second strut and a third strut, and the first strut is oriented at a first clocking angle, wherein the first clocking angle is disposed between the major axis of the first strut and a first radial line that extends from the axial centerline and intersects the cross-section geometry center of the first strut, and the second strut is oriented at a second clocking angle, wherein the second clocking angle is disposed between the major axis of the second strut and a second radial line that extends from the axial centerline and intersects the cross-section geometry center of the second strut, wherein the second clocking angle is not equal to the first clocking angle, wherein the third strut is oriented at a third clocking angle, wherein the third clocking angle is disposed between the major axis of the third strut and a third radial line that extends from the axial centerline and intersects the cross-section geometry center of the third strut, and the third clocking angle is not equal to the first clocking angle or the second clocking angle;

wherein the plurality of struts are non-uniformly circumferentially spaced within the air intake plenum;

wherein the air intake plenum includes an air inlet; and

wherein a majority of the struts within the plurality of struts are disposed within the air intake plenum in a portion of the air intake plenum disposed on an opposite side of the axial centerline than the air inlet.

2. A gas turbine engine, comprising:

an axial centerline;

at least one compressor rotor stage having a first bladed rotor rotatable about the axial centerline;

at least one turbine rotor stage having a second bladed rotor rotatable about the axial centerline; and

an air intake plenum in communication with the at least one compressor rotor stage, the air intake plenum including:

a first gas path surface;

a second gas path surface, spaced apart from the first gas path surface, wherein the first gas path surface and the second gas path surface define at least a portion of a plenum interior configured for air passage; and

a plurality of struts that extend lengthwise between the first gas path surface and the second gas path surface through the plenum interior, each strut having a cross-section geometry within a plane perpendicular to a lengthwise axis of the strut, the cross-section geometry having a cross-section geometry center, a major axis, and a minor axis, where the major axis is greater than the minor axis, wherein the cross-section geometry is the same for each strut, and the cross-section geometry center disposed at an intersection of the major axis and the minor axis, and the cross-section is symmetrical about the cross-section geometry center;

wherein the plurality of struts are disposed circumferentially spaced apart from one another within the air intake plenum, and the plurality of struts are disposed circumferentially around the axial centerline; and

wherein the plurality of struts includes a first strut, a second strut and a third strut, and the first strut is oriented at a first clocking angle, wherein the first clocking angle is disposed between the major axis of the first strut and a first radial line that extends from the axial centerline and intersects the cross-section geometry center of the first strut, and the second strut is oriented at a second clocking angle, wherein the second clocking angle is disposed between the major axis of the second strut and a second radial line that extends from the axial centerline and intersects the cross-section geometry center of the second strut, wherein the second clocking angle is not equal to the first clocking angle, wherein the third strut is oriented at a third clocking angle, wherein the third clocking angle is disposed between the major axis of the third strut and a third radial line that extends from the axial centerline and intersects the cross-section geometry center of the third strut, the third clocking angle is not equal to the first clocking angle or the second clocking angle;

wherein the plurality of struts are non-uniformly circumferentially spaced within the air intake plenum;

wherein the air intake plenum includes an air inlet; and

wherein a majority of the struts within the plurality of struts are disposed within the air intake plenum in a portion of the air intake plenum disposed on an opposite side of the axial centerline than the air inlet.

3. An air intake plenum for a gas turbine engine, comprising:

an axial centerline;

an air inlet;

a first gas path surface;

a second gas path surface, spaced apart from the first gas path surface, wherein the first gas path surface and the second gas path surface define at least a portion of a plenum interior configured for air passage; and

a plurality of struts that extend lengthwise between the first gas path surface and the second gas path surface through the plenum interior, each strut having a cross-section geometry within a plane perpendicular to a lengthwise axis of the strut, the cross-section geometry having a cross-section geometry center, a major axis, and a minor axis, where the major axis is greater than the minor axis;

wherein the plurality of struts are disposed non-uniformly circumferentially spaced apart from one another within the air intake plenum, and a majority of the struts within the plurality of struts are disposed within the air intake plenum in a portion of the air intake plenum disposed on an opposite side of the axial centerline than the air inlet; and

wherein the plurality of struts includes a first strut and a second strut, and the first strut is oriented at a first clocking angle, wherein the first clocking angle is disposed between the major axis of the first strut and a first radial line that extends from the axial centerline and intersects the cross-section geometry center of the first strut, and the second strut is oriented at a second clocking angle, wherein the second clocking angle is disposed between the major axis of the second strut and a second radial line that extends from the axial centerline and intersects the cross-section geometry center of the second strut, wherein the second clocking angle is not equal to the first clocking angle.

Assignments (1)

Continuity (2)

References Cited (9)