Back to results
US 11,952,943 B2Granted
Assembly for a compressor section of a gas turbine engine
AssigneePratt & Whitney Canada Corp.
InventorsKaran Anand, Hong Yu
Life of this patent
Estimating the term…
Abstract
Assemblies and methods for directing a flow of air through a compressor section of a gas turbine engine are disclosed. A method includes receiving the flow of air over a strut extending radially across a substantially annular gas path of the gas turbine engine, and at least partially confining and modifying a strut wake generated in the flow of air by the strut using one or more variable orientation guide vanes.
Claims13
An assembly for a compressor section of a gas turbine engine, the assembly comprising:
- an outer shroud and an inner shroud defining a substantially annular gas path therebetween, the gas path having a central axis and extending axially along the central axis;
- a plurality of struts extending radially in the gas path, the struts being angularly spaced-apart around the central axis, two adjacent struts defining a strut passage therebetween, the strut passage extending axially along the central axis between leading edges of the two adjacent struts and trailing edges of the two adjacent struts;
- and
- a plurality of variable orientation guide vanes extending radially in the gas path, the variable orientation guide vanes being uniformly angularly spaced-apart around the central axis, two adjacent variable orientation guide vanes of the plurality of variable orientation guide vanes having a leading edge axially overlapping the strut passage at one or more orientations of the two adjacent variable orientation guide vanes,
- wherein:
- one of the plurality of struts is angularly positioned between the two adjacent variable orientation guide vanes;
- a first of the two adjacent variable orientation guide vanes is pivotable about a pivot point;
- and
- a first angular spacing between the one strut and the first of the two adjacent variable orientation guide vanes is greater than a chordwise distance between the leading edge of the first of the two adjacent variable orientation guide vanes and the pivot point.
6 more elements
A gas turbine engine comprising:
- a compressor for pressurizing air;
- a combustor in which compressed air from the compressor is mixed with fuel and ignited for generating a stream of hot combustion gases;
- and
- a turbine section for extracting energy from the combustion gases;
- the compressor including:
- a substantially annular gas path having a central axis and extending axially along the central axis;
- a strut extending radially in the gas path;
- a strut passage defined in the gas path, the strut passage extending axially along the central axis between a leading edge of the strut and a trailing edge of the strut;
- a plurality of variable orientation guide vanes extending radially in the gas path, the variable orientation guide vanes being uniformly angularly spaced-apart around the central axis, two adjacent variable orientation guide vanes of the plurality of variable orientation guide vanes having a leading edge axially overlapping the strut passage and a trailing edge disposed downstream of the strut passage at one or more orientations of the two adjacent variable orientation guide vanes;
- and
- a rotor disposed downstream of the plurality of variable orientation guide vanes and configured to compress the air,
- wherein:
- the strut is angularly positioned between the two adjacent variable orientation guide vanes of the plurality of variable orientation guide vanes;
- a first of the two adjacent variable orientation guide vanes is pivotable about a pivot point;
- and
- a first angular spacing between the strut and the first of the two adjacent variable orientation guide vanes is greater than a chordwise distance between the leading edge of the first of the two adjacent variable orientation guide vanes and the pivot point.
13 more elements
Dependencies are inferred from the claim text.