Assembly for a compressor section of a gas turbine engine
AssigneePratt & Whitney Canada Corp.
InventorsKaran ANAND, Hong YU
Life of this patent
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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.
Claims20
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 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 uniformly angularly spaced-apart around the central axis, one or more of the variable orientation guide vanes having a leading edge axially overlapping the strut passage at one or more orientations of the one or more of the variable orientation guide vanes.
A gas turbine engine comprising:
- a compressor for pressurizing air;
- a combustor in which the compressed air 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 uniformly angularly spaced-apart around the central axis, one or more of the 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 one or more of the variable orientation guide vanes;
- and
- a rotor disposed downstream of the plurality of variable orientation guide vanes and configured to compress the air.
A method of directing a flow of air through a compressor section of a gas turbine engine, the method comprising:
- receiving the flow of air over a strut extending radially across a substantially annular gas path of the gas turbine engine, the gas path having a central axis;
- at least partially confining a strut wake generated in the flow of air by the strut, the strut wake being at least partially confined between two adjacent variable orientation guide vanes angularly spaced-apart from the strut, the variable orientation guide vanes axially overlapping a portion of the strut relative to the central axis;
- and
- modifying the strut wake using at least one of the two variable orientation guide vanes.
Dependencies are inferred from the claim text.