Air inlet strut for aircraft engine

Patent metadata

Field	Value
Publication number	US-11719165-B2
Application number	US-202117453387-A
Country	US
Kind code	B2
Filing date	Nov 3, 2021
Priority date	Nov 3, 2021
Publication date	Aug 8, 2023
Grant date	Aug 8, 2023

Abstract

An aircraft engine comprises an air inlet duct extending from an inlet through which air is configured to enter the aircraft engine, to an outlet within the aircraft engine. At least one strut has a leading edge and a trailing edge and extends across at least part of the air inlet duct. The at least one strut has a strut passage and a plurality of static pressure measurement taps spaced apart on the trailing edge and in fluid communication with the strut passage.

First claim

The invention claimed is:

1. An aircraft engine, comprising:
an air inlet duct extending from an inlet through which air is configured to enter the aircraft engine to an outlet within the aircraft engine; and
at least one strut having a leading edge and a trailing edge and extending across at least part of the air inlet duct, the at least one strut having a strut passage and a plurality of static pressure measurement taps spaced apart on the trailing edge and in fluid communication with the strut passage via a plurality of measurement tap passages, the strut passage having a radially innermost point positioned at a radially outermost point of a radially innermost measurement tap passage of the plurality of measurement tap passages.

2. The aircraft engine of claim 1 , wherein the air inlet duct extends in a direction radial to a center axis of the aircraft engine, the outlet positioned radially inwardly of the inlet, and the leading edge of the at least one strut positioned radially closer to the inlet than the trailing edge.

3. The aircraft engine of claim 1 , wherein the trailing edge of the at least one strut has a plurality of edge contours, each edge contour of the plurality of edge contours positioned at one static pressure measurement tap of the plurality of static pressure measurement taps, each edge contour of the plurality of edge contours defining a contour edge wall recessed from a remainder of the trailing edge.

4. The aircraft engine of claim 1 , wherein the strut passage and the plurality of measurement tap passages slope toward a center axis of the aircraft engine.

5. The aircraft engine of claim 1 , wherein a length of each measurement tap passage of the plurality of measurement tap passages is defined between a first end at the strut passage and a second end at the trailing edge of the at least one strut, a ratio of the length over a diameter of one static measurement tap of the plurality of static measurement taps being greater than three.

6. The aircraft engine of claim 1 , wherein the at least one strut includes a plurality of struts extending across the at least part of the air inlet duct and spaced circumferentially apart, the plurality of struts include a top strut, the plurality of static measurement taps positioned on the trailing edge of the top strut.

7. The aircraft engine of claim 1 , wherein the plurality of static pressure measurement taps includes a first static pressure measurement tap and a second static pressure measurement tap, the first static pressure measurement tap positioned adjacent to one of a root and a tip of the at least one strut at the trailing edge, the second static pressure measurement tap positioned adjacent to the other of the root and the tip at the trailing edge.

8. The aircraft engine of claim 7 , wherein the trailing edge has a span measured between the root and the tip, the first and second static pressure measurement taps spaced apart along the trailing edge a distance not less than 40% of the span.

9. An aircraft engine, comprising:
an engine casing having an annular wall about a center axis of the aircraft engine, and an air inlet duct extending from an opening in the annular wall to an outlet of the air inlet duct radially inward of the annular wall; and
at least one strut extending across the air inlet duct and between a leading edge and a trailing edge, the at least one strut having a strut passage extending within the at least one strut and a plurality of static pressure measurement taps spaced apart on the trailing edge and in fluid communication with the strut passage via a plurality of measurement tap passages, the strut passage having a radially innermost point positioned at a radially outermost point of a radially innermost measurement tap passage of the plurality of measurement tap passages.

10. The aircraft engine of claim 9 , wherein the trailing edge of the at least one strut has a plurality of edge contours, each edge contour of the plurality of edge contours positioned at one static pressure measurement tap of the plurality static pressure measurement taps, each edge contour of the plurality of edge contours defining a contour edge wall recessed from a remainder of the trailing edge.

11. The aircraft engine of claim 9 , wherein the strut passage and the plurality of measurement tap passages slope toward the center axis.

12. The aircraft engine of claim 9 , wherein a length of each measurement tap passage of the plurality of measurement tap passages is defined between a first end at the strut passage and a second end at the trailing edge of the at least one strut, a ratio of the length over a diameter of one static measurement tap of the plurality of static measurement taps being greater than three.

13. The aircraft engine of claim 9 , wherein the at least one strut includes a plurality of struts extending across the air inlet duct and spaced circumferentially apart, the plurality of struts include a top strut, the plurality of static measurement taps positioned on the trailing edge of the top strut.

14. The aircraft engine of claim 9 , wherein the plurality of static pressure measurement taps includes a first static pressure measurement tap and a second static pressure measurement tap, the first static pressure measurement tap positioned adjacent to one of a root and a tip of the at least one strut at the trailing edge, the second static pressure measurement tap positioned adjacent to the other of the root and the tip at the trailing edge.

15. The aircraft engine of claim 14 , wherein the trailing edge has a span measured between the root and the tip, the first and second static pressure measurement taps spaced apart along the trailing edge a distance not less than 40% of the span.

Assignees

• Pratt & Whitney Canada

Inventors

• Le Pape Damien
• Yan Guorong
• Cunningham Mark
• Beauchesne-Martel Philippe
• Iskra Oleg
• Ivakitch Richard

Classifications

• F02C7/32 Primary

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

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F01D17/08 Primary

  responsive to condition of working-fluid, e.g. pressure · CPC title

• F02C7/04

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