Integrated strut and IGV configuration

Patent metadata

Field	Value
Publication number	US-10808556-B2
Application number	US-201816122295-A
Country	US
Kind code	B2
Filing date	Sep 5, 2018
Priority date	Mar 13, 2014
Publication date	Oct 20, 2020
Grant date	Oct 20, 2020

Abstract

A strut and IGV configuration in a gas turbine engine positioned at an upstream of a rotor includes a plurality of radial struts, for example for bearing engine loads, and a plurality of inlet guide vanes positioned axially spaced apart from the struts. The number of inlet guide vanes is greater than the number of struts. The struts are circumferentially aligned with the inlet guide vanes.

First claim

The invention claimed is:

1. A method of providing an aircraft gas turbine engine, the method comprising:
providing a plurality of circumferentially-spaced struts radially extending across an inlet flow passage leading to an engine rotor, the plurality of circumferentially-spaced struts bearing structural loads of the aircraft gas turbine engine;
providing a plurality of variable inlet guide vanes between the struts and the rotor, the number of variable inlet guide vanes being greater than the number of struts, wherein each of the plurality of variable inlet guive vanes is individually rotatable about a respective rotation axis; and
circumferentially positioning the variable inlet guide vanes to allow the struts to circumferentially align with a respective one of the variable inlet guide vanes; including:
during a design phase of the aircraft gas turbine engine, setting a position of the respective rotation axis of each variable inlet guide vane of the plurality of variable inlet guide vanes such that in use a flow direction of air passing around each strut of the plurality of circumferentially-spaced struts forms a respective strut wake which is then substantially redirected by a correspondingly aligned variable inlet guide vane of the plurality of variable inlet guide vanes when the correspondingly aligned variable inlet guide vane is in a maximum setting angle or in a design point setting angle, including selecting a chordwise position of the respective rotation axis of each variable inlet guide vanes of the plurality of variable inlet guide vanes between a leading edge and a trailing edge of each of the plurality of variable inlet guide vanes so that the plurality of variable inlet guide vanes substantially block the respective strut wakes downstream of the struts at both the design point setting angle and the maximum setting angle.

2. The method as defined in claim 1 further comprising: determining a chord length of the respective variable inlet guide vanes in a range of 10% to 200% of an axial gap between the struts and the variable inlet guide vanes.

3. The method as defined in claim 1 further comprising: determining a chord length of the respective variable inlet guide vanes in a range of 30% to 100% of an axial gap between the struts and the variable inlet guide vanes.

4. The method as defined in claim 1 further comprising: determining a chord length of said one of the variable inlet guide vanes circumferentially aligned with the respective struts, greater or smaller than a chord length of the remaining variable inlet guide vanes.

5. The method as defined in claim 1 wherein providing a plurality of variable inlet guide vanes includes: determining the number of the variable inlet guide vanes to be a multiple of the number of the struts.

6. The method as defined in claim 5 wherein circumferentially positioning the variable inlet guide vanes: includes positioning the variable inlet guide vanes to be circumferentially evenly spaced apart.

7. The method as defined in claim 1 wherein circumferentially positioning the variable inlet guide vanes includes: positioning the variable inlet guide vanes to be circumferentially unevenly spaced apart when the number of the variable inlet guide vanes is not a multiple of the number of the struts.

Assignees

• Pratt & Whitney Canada

Inventors

• Yu Hong
• Dutton Ronald

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F01D25/162

  Bearing supports · CPC title

• B23P15/006

  turbine wheels · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F04D29/544

  Blade shapes · CPC title