Honeywell International Inc.

Peter Hall

Bruce David Reynolds

Richard David Conner

Timothy Gentry

Mark C Morris

Yogendra Y Sheoran

Shawn Alstad

John Repp

Doug Hollingshead

Alan Tiltman

Don Weir

Manuel Sandoval

Ryan Bonde

Coleen Anne Cramer

Robert Burkhead

Rotor systems and methods for improved performance with extended range to stall fabricated through the use of additive manufacturing. A rotor has blades that extend to tips and rotates about an axis. A casing fits over the rotor so that the tips are configured to pass proximate the casing when the rotor rotates. The casing channels a flow stream across the rotor. Grooves are defined in the casing and extend longitudinally at an acute angle relative to the axis. The grooves extend a distance upstream from a leading edge of the blades and over at least a portion of the blade tips so that the blade tips are configured to pass across the grooves when the rotor rotates.

Grooved rotor casing system using additive manufacturing method

A turbine nozzle for a gas turbine engine includes an outer endwall, and an inner endwall spaced apart from the outer endwall. The turbine nozzle includes at least one airfoil coupled between the inner endwall and the outer endwall, and a compliant joint defined in at least one of the outer endwall and the inner endwall. The compliant joint includes at least one partially-fused seal that is configured to restrict a flow of fluid through the at least one of the outer endwall and the inner endwall and to form a slip-joint above a predetermined threshold stress. The slip-joint is configured to maintain a radial position of the at least one of the outer endwall and the inner endwall.

Turbine nozzle with compliant joint

A fan structure having integrated rotor impeller, and methods of producing the same are provided. The fan structure includes a fan housing that encircles a longitudinal axis, and defines an airflow direction from an inlet side to an exit side. The integrated rotor impeller structure is disposed to rotate within the fan housing. The integrated rotor impeller structure includes (a) a cylindrical rotor shell being annular about the longitudinal axis, and having a shell length, and (b) an axis rod coaxial with the longitudinal axis, and having an axis rod length of less than or equal to the shell length. An airflow annulus is created therebetween. A blade is disposed within the airflow annulus to extend radially from the external surface of the axis rod to the inside surface of the the cylindrical rotor shell. One or more magnets are integrated within the integrated rotor impeller structure.

Fan structure having integrated rotor impeller, and methods of producing the same

A stator attachment system couples a stator to a compressor case that is split to define a first half and a second half. The stator attachment system includes a plurality of retention slots defined in each of the first half and the second half of the compressor case. The plurality of retention slots is spaced apart about a perimeter of the first half and the second half such that at least one of the plurality of retention slots associated with the first half is vertically aligned with at least one of the plurality of retention slots associated with the second half. The stator attachment system includes a plurality of tabs defined on the stator that extend radially outward from the stator. Each of the plurality of tabs is configured to engage with one of the plurality of retention slots to couple the stator to the compressor case.

Stator attachment system for gas turbine engine

Variable vane devices containing rotationally-driven translating vane structures are provided, as are methods for fabricating variable vane devices. In one embodiment, the variable vane device includes a flow assembly having a centerline, an annular flow passage extending through the flow assembly, cam mechanisms, and rotationally-driven translating vane structures coupled to the flow assembly and rotatable relative thereto. The translating vane structures include vane bodies positioned within the annular flow passage and angularly spaced about the centerline. During operation of the variable vane device, the cam mechanisms adjust translational positions of the vane bodies within the annular flow passage in conjunction with rotation of the translating vane structures relative to the flow assembly. By virtue of the translational movement of the translating vane structures, a reduction in the clearances between the vane bodies and neighboring flow assembly surfaces can be realized to reduce end gap leakage and boost device performance.

Variable vane devices containing rotationally-driven translating vane structures and methods for the production thereof

An inlet assembly for a turboprop engine system is provided. The inlet assembly includes an inlet plenum defining first inlet configured to receive air from the atmosphere; an expansion plenum coupled to the inlet plenum and configured to receive the air from the inlet plenum, the inlet plenum and the expansion plenum defining a flow path for the air with a bend of at least 90&#xb0;; and a second inlet coupled to the expansion plenum and configured to receive the air from the expansion plenum.

Growing community of inventors

Phoenix, AZ, United States of America

Peter Hall