General Electric Company

Gregory John Kajfasz

Brian Chandler Barr

Brian Keith

Anthony Louis DiPietro, Jr

Prem Venugopal

Aamir Shabbir

Matthew F Adam

Brian David Keith

Gas turbine engines having moveable inlet guide vanes and stator vanes are described herein. An example gas turbine engine includes a casing defining a flow passageway to a compressor. The casing includes an outer radial wall and an inner radial wall. The compressor includes alternating stages of rotor blades and stator vanes in the flow passageway. The gas turbine engine also includes an inlet guide vane in the flow passageway upstream of a first stage of rotor blades of the compressor. The inlet guide vane extends between the outer radial wall and the inner radial wall. The inlet guide vane includes an outer radial panel coupled to the outer radial wall, an inner radial panel coupled to the inner radial wall, and a middle panel between the outer radial panel and the inner radial panel. The middle panel is rotatable relative to the outer and inner radial panels.

Gas turbine engines having moveable inlet guide vanes and stator vanes

A compressor apparatus includes: a rotor including: a disk mounted for rotation about a centerline axis, an outer periphery of the disk defining a flowpath surface having an non-axisymmetric surface profile; an array of airfoil-shaped axial-flow compressor blades extending radially outward from the flowpath surface, wherein the compressor blades each have a root, a tip, a leading edge, and a trailing edge; and an array of airfoil-shaped splitter blades alternating with the compressor blades, wherein the splitter blades each have a root, a tip, a leading edge, and a trailing edge; and wherein at least one of a chord dimension of the splitter blades at the roots thereof and a span dimension of the splitter blades is less than the corresponding dimension of the compressor blades.

Axial compressor rotor incorporating non-axisymmetric hub flowpath and splittered blades

A compressor apparatus includes: a rotor having: a disk mounted for rotation about a centerline axis, an outer periphery of the disk defining a flowpath surface; an array of airfoil-shaped axial-flow compressor blades extending radially outward from the flowpath surface, wherein the compressor blades each have a root, a tip, a leading edge, and a trailing edge, wherein the compressor blades have a chord dimension and are spaced apart by a circumferential spacing, the ratio of the chord to the circumferential spacing defining a blade solidity parameter; and an array of airfoil-shaped splitter blades alternating with the compressor blades, wherein the splitter blades each have a root, a tip, a leading edge, and a trailing edge; wherein at least one of a chord dimension of the splitter blades at the roots thereof and a span dimension of the splitter blades is less than the corresponding dimension of the compressor blades.

Axial compressor rotor incorporating splitter blades

A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform has a scalloped flow surface including a purge trough commencing tangentially in a blend area of the platform. The purge trough extending axially toward the suction side of the airfoil, aft of the leading edge, to channel a purge flow.

Scalloped surface turbine stage with purge trough

A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. At least some of the platforms have a scalloped flow surface including a bulge adjoining the pressure side and a bowl adjoining the suction side, aft of the leading edge, of the respective airfoils. The bulge is configured having a maximum height located within its respective flow passage, and wherein the bulge decreases in height in a forward and aft direction and decreases in height laterally toward the pressure side of the airfoil and toward the bowl adjoining the suction side of a next adjacent airfoil.

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Cincinnati, OH, United States of America

Gregory John Kajfasz