Rtx Corporation

Raytheon Technologies Corporation

Other

United Technologies Corporation

Simon W Evans

Michael M Joly

Zaffir A Chaudhry

Yuan Dong

Sean Nolan

Michael Steven DeMers

Georgi Kalitzin

Andrzej Ernest Kuczek

Dilip Prasad

Brandon M Evans

Gorazd Medic

Neil J Terwilliger

Jon E Sobanski

Om Parkash Sharma

Christopher J Hanlon

Dmytro Mykolayovych Voytovych

Sue-Li Chuang

Robert W Fessenden

Li Xing Pan

Gorzad Medic

Sue-Li Kingsley Chuang

A turbine engine is provided that includes a propulsor rotor and an engine core. The propulsor rotor is rotatable about a propulsor axis. The engine core is configured to power operation of the propulsor rotor. The engine core includes a core compressor section, a core combustor section, a core turbine section, a first rotating structure and a second rotating structure. The first rotating structure includes a first compressor rotor arranged within the core compressor section. The first rotating structure is rotatable about a first structure axis which is offset from the propulsor rotor axis. The second rotating structure includes a second compressor rotor arranged within the core compressor section. The second rotating structure is rotatable about a second structure axis which is offset from the propulsor rotor axis and the first structure axis.

Aircraft propulsion system engine with multiple independent rotating structures

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 propulsion system for an aircraft includes an intercooling system configured to inject water into a compressor section to reduce a temperature of a core airflow within the core flow path. The intercooling system includes a plurality of injectors for injecting water at a water injection angle relative to an airflow to generate a defined swirl of a combined airflow and water to the compressor section.

Fluidic compressor inlet guide vane

A propulsion system is provided for an aircraft. This propulsion system includes a turbine engine, and the turbine engine includes a propulsor rotor, an engine core and a heat exchanger. The propulsor rotor is configured to rotate about an axis and direct a first air stream along a primary flowpath that bypasses the engine core. The propulsor rotor is configured to direct a second air stream along a secondary flowpath with a geometry extending at least eighty degrees about the axis. The turbine engine is configured such that the first air stream enters the primary flowpath at a first pressure and the second air stream enters the secondary flowpath at a second pressure that is different than the first pressure. The engine core is configured to drive rotation of the propulsor rotor. The heat exchanger is disposed within the secondary flowpath.

Pressure control for bifurcated flow of a turbine engine

A propulsion system for an aircraft includes an intercooling system with a plurality of injectors for injecting an intercooling waterflow into a portion of a compressor passage. The plurality of injectors are spaced apart about the compressor passage and the injection of the intercooling water flow is varied between the plurality of injectors to influence flow that is communicated through the compressor passage.

Fluidic compressor inlet guide vanes

A compressor section for a gas turbine engine includes a blade including a platform, a tip and an airfoil extending between the platform and tip. The airfoil includes a root portion adjacent to the platform, a midspan portion and a tip portion. Each of the root portion, midspan portion and tip portion define a meridional velocity at stage exit with the tip portion including a first meridional velocity greater than a second meridional velocity of the midspan portion. A blade for an axial compressor of a gas turbine engine and a method of operating a compressor section of a gas turbine engine are also disclosed.

Repeating airfoil tip strong pressure profile

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 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 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.

Inclination of forward and aft groove walls of casing treatment for gas turbine engine

A rotor blade of a gas turbine engine includes a pressure side, and a suction side opposite the pressure side and defining a rotor blade profile therebetween, the pressure side and the suction side each extending from a blade root to a blade tip. The rotor blade defines a cross-sectional median line midway between the pressure side and the suction side. The cross-sectional median line extends in a generally radial direction from the blade root to a lean point between the blade root and the blade tip. The cross-sectional median line extends off of radial from the lean point to the blade tip, defining a lean of the rotor blade between the lean point and the blade tip.

Local pressure side blade tip lean

The herein described invention is a camera mounting system where the user can safely install a camera high in a tree without having to leave the ground. The camera mounting system is comprised of a tree attachment, ball mount, and camera mount. The system is installed by using an extension pole with releasable capture means for installation and removal of the system. This system is also comprised of a multi-mount adapter, which allows a user to install multiple wire connected mounted components on one tree attachment, or in different elevated positions. Once installed, a camera can be accurately aimed by using a laser attachment and standard laser pen light. This system is further comprised of a saw attachment, which can be used to clear branches from the installation area of the tree being utilized.

Trail camera mounting system

The herein described invention is a camera mounting system where the user can safely install a camera high in a tree without having to leave the ground. The camera mounting system is comprised of a tree attachment, ball mount, and camera mount. The system is installed by using an extension pole with releasable capture means for installation and removal of the system. Once installed, a camera can be accurately aimed by using a laser attachment and standard laser pen light. This system is further comprised of a saw attachment, which can be used to clear branches from the installation area of the tree being utilized.

Rotor of a gas turbine engines having a rotor hub and a plurality of blades extending from the rotor hub, wherein each blade has a full-span forward sweep along a leading edge of the blade that starts at an airfoil root of the blade at the hub and extends to a blade tip, wherein a sweep of a blade is a percentage of a root axial chord length of the respective blade.

Full-span forward swept airfoils for gas turbine engines

A two-piece mounting system for a trail camera has a support with a fitting that is placed high in a tree on a tree branch. The support with an auger anchor is driven into the tree branch with an extension pole equipped with a companion fitting. The auger has a releasable spring-loaded turn-to-lock capture means to capture and hold a utility bar. The utility bar, like the auger support, is placed and attached to the support with the extension pole. The utility bar receives a universal camera mount attached to the bar through a swivel. The camera mount and swivel have an adjustment bar that has a fitting that can be received by the extension pole fitting, so once placed in the tree, the camera angle can be adjusted.

Growing community of inventors

Farmington, CT, United States of America

Simon W Evans