Carrier Corporation

Raytheon Technologies Corporation

Rtx Corporation

Michael M Joly

Vishnu Mohan Sishtla

William T Cousins

Zaffir A Chaudhry

Simon W Evans

Gorazd Medic

Chaitanya Vishwajit Halbe

Andrzej Ernest Kuczek

Dilip Prasad

Georgi Kalitzin

Byron R Monzon

Jason Elliott

Xuetao Li

Bronwyn Power

Christopher Beaudry Miller

Om Parkash Sharma

Dmytro Mykolayovych Voytovych

Xiaodan Cai

Gorzad Medic

A gas turbine engine is provided and includes a first fan blade including a suction surface, a second fan blade comprising a pressure surface and neighboring the first fan blade and a throat region interposed between the suction surface of the first fan blade and the pressure surface of the second fan blade. The throat region includes a passage throat located at a minimum distance between the pressure and suction surfaces. The first and second fan blades are configured such that a pre-compression region is defined in the throat region ahead of the passage throat. Each of the first and second fan blades includes a mean camber line defining a flattened suction surface.

Fan blade or vane with improved bird impact capability

An airfoil for a gas turbine engine including an airfoil body extending between a leading edge and a trailing edge and between a pressure side and a suction side. The airfoil body includes a strut portion extending from the leading edge and a flap portion extending from the trailing edge. The flap portion is pivotable relative to the strut portion. A flexible skin surrounds both the strut portion and the flap portion on both the pressure side and the suction side.

Morphing structures for fan inlet variable vanes

A compressor includes a housing, a first compression stage defined within the housing, a second compression stage defined within the housing, and a motor disposed between the first compression stage and the second compression stage relative to a flow of fluid through the compressor. The first compression component of the first compression stage has a mixed-flow configuration and the second compression component of the second compression stage has a radial-flow configuration.

Refrigeration system mixed-flow compressor

A refrigerant compressor assembly (A,B,C) includes an axial compressor (B,C,) that includes at least one axial stage. A downstream compressor () is located fluidly downstream of the axial compressor (B,C,) and includes one of a mixed-flow impeller () or a centrifugal impeller (). At least one motor () is in driving engagement with at least one of the axial compressor (B,C,) and the downstream compressor ().

Axial and downstream compressor assembly

An apparatus is provided for a gas turbine engine. This engine apparatus includes an airfoil extending spanwise along a span line from a base to a tip. The airfoil extends laterally between a pressure side and a suction side. The airfoil extends longitudinally along a camber line from a leading edge to a trailing edge. The airfoil includes a first section and a second section arranged longitudinally between the first section and the trailing edge along the camber line. An angle between the camber line and a reference plane changes according to a slope as the airfoil extends longitudinally along the camber line. The slope in the second section is greater than the slope in the first section.

Gas turbine engine airfoil with extended laminar flow

A gas turbine engine includes a fan section, a compressor section, and a turbine section. The fan section has a plurality of vane assemblies spaced circumferentially about an engine axis. The vane assemblies each include an airfoil extending between a leading edge and a trailing edge, a control rod extending through the airfoil, and a mechanism driven by the control rod to change the shape of the airfoil. A vane system for a gas turbine engine is also disclosed.

A mixed-flow compressor includes an impeller attached to a shaft and rotatable about a shaft axis. A vaneless diffuser is located axially downstream of the impeller and has a converging portion and a diverging portion. A vaned diffuser is located axially downstream of the vaneless diffuser.

Vaneless supersonic diffuser for compressor

A centrifugal compressor includes a casing. An impeller is arranged within the casing. The impeller is rotatable about an axis. A diffuser section is arranged within the casing. The diffuser section is positioned axially downstream from an outlet of the impeller and includes a forward portion fixed relative to the impeller and an aft portion distinct from the forward portion.

Mixed-flow compressor configuration for a refrigeration system

A compressor includes a housing. An impeller is located within the housing and rotatable about an impeller axis in a first rotational direction. A rotor section is rotatable about the impeller axis in a second rotational direction opposite the first rotational direction.

Mixed-flow compressor with counter-rotating diffuser

An impeller mountable within a centrifugal compressor includes a hub having a front side and a back side, the hub being rotatable about an axis of rotation and a plurality of vanes extending outwardly from the front side of the hub such that a plurality of passages is defined between adjacent vanes. The plurality of vanes is oriented such that a flow output from the plurality of passages adjacent the back side of the impeller is arranged at an angle to the axis of rotation of less than 20 degrees.

A centrifugal compressor includes a shaft defining an axis, an impeller mounted to the shaft for rotation about the axis, and a diffuser section including a first wall, a second wall, and an opening defined between the first wall and the second wall. The opening of the diffuser section is arranged in fluid communication with the impeller. The first wall is rotatable about the axis and rotation of the first wall about the axis is mechanically driven.

Rotating diffuser in centrifugal compressor

A stator vane for a gas turbine engine section includes a stator vane having an airfoil extending between a leading edge and a trailing edge. The airfoil has a suction side and a pressure side. There is at least one piezoelectric actuator for changing a shape of at least one of the leading edge and the trailing edge. A gas turbine engine is also disclosed.

Gas turbine engine with morphing variable compressor vanes

A gas turbine engine includes a plurality of blades circumferentially spaced from each other. A plurality of rings are spaced radially outward from the plurality of blade. At least one actuator is in mechanical communication with the plurality of rings for moving the plurality of rings in an axial direction to create an axial gap adjacent at least one of the plurality of rings.

Adaptive case for a gas turbine engine

A compressor for use in a gas turbine engine including: an airfoil configured to rotate about an engine central longitudinal axis of the gas turbine engine; a casing, the casing including a radially inward surface; and a groove located within the casing opposite the airfoil, the groove is recessed in a radially outward direction from the radially inward surface of the casing, wherein the groove is defined by a forward groove wall, an aft groove wall opposite the forward groove wall, and a base groove interposed between the forward groove wall and the aft groove wall, and wherein the forward groove wall is operably shaped to generate an aft directed jet.

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Hebron, CT, United States of America

Michael M Joly