General Electric Company

Novartis Ag

General Electric Company Polska Sp. Z O.o.

Vinod Shashikant Chaudhari

Bhaskar Nanda Mondal

Thomas Ory Moniz

David William Crall

Dirk Behnke

Claudia Betschart

Chetan Pandit

Simona Cotesta

Sangamesh Badiger

Greedaran Kubendran Jankin

Ravindra Shankar Ganiger

Jeffrey Douglas Rambo

Trevor Howard Wood

Kishore Ramakrishnan

Ian Francis Prentice

Praveen Sharma

Rajesh Kumar

Sandeep Kumar

Tsuguji Nakano

Dattu G V Jonnalagadda

Jürgen Wagner

Mohan Kannaiah Raju

Silvio Ofner

Shivam Mittal

Ramana Reddy Kollam

Pradeep Hemant Sangli

Merin Sebastian

Samuel Hintermann

Bhujabal Prashant Mahadeo

Murali Chebrolu

Santosh Kumar Potnuru

Kishanjit Pal

Rachamadugu Sivaprasad

Sushilkumar Shevakari

Neil Fraser Cunningham

Jürgen Hans-Hermann Hinrichs

Sivakumar Mahesh

Arndt Meyer

Jagadisha Pai Nagarmat

Michal Starzynski

Sangamesch Badiger

Simona Costesta

A rotor blade assembly for a turbine engine, including an airfoil blade including an inner diameter end and an outer diameter end, a lower blade carrier coupled to the inner diameter end of the airfoil blade and rigidly coupled to a disk via a pin, an upper blade carrier coupled to the outer diameter end of the airfoil blade, and an outer drum coupled to the upper blade carrier via a radial joint. The radial joint supports radial motion of the upper blade carrier relative to an axis extending through a center of the rotor blade assembly.

Rotor blade assemblies for turbine engines

An unducted single fan engine includes a housing having one or more fan blades coupled to the housing and configured to rotate circumferentially. The engine has one or more outlet guide vanes coupled to the housing. Each of the one or more guide vanes has a leading edge portion having a variable leading edge. The engine has one or more actuation devices coupled to each of the one or more outlet guide vanes. The one or more actuation devices are configured to control the variable leading edge of the respective outlet guide vane. The variable leading edge is controllable to vary the pitch, camber, lean angle, or sweep of the respective outlet guide vane.

Outlet guide vane

Structures, such as compressor casings, for reducing a thermal gradient are provided. For example, a compressor case is split such that it includes first and second case segments. The first case segment extends over a first portion of the compressor case circumference and comprises a first inner structure, a first outer structure, and a first porous structure integrally formed as a monolithic component. The first porous structure is defined between the first inner structure and the first outer structure. The second case segment extends over a second portion of the compressor case circumference and comprises a second inner structure, a second outer structure, and a second porous structure integrally formed as a monolithic component. The second porous structure is defined between the second inner structure and the second outer structure. Methods of cooling structures such as compressor casings also are provided.

Split casings and methods of forming and cooling casings

Methods, apparatus, systems and articles of manufacture for compact compressors are disclosed including a gas turbine engine defining an axial direction and a radial direction, the gas turbine engine including an axial flow compressor and a radial flow compressor, wherein the axial flow compressor is located axially forward of the radial flow compressor, a blade assembly including a splitter shroud to divide incoming air into axial air flow for the axial flow compressor and radial air flow for the radial flow compressor, the blade assembly rotating relative to the axial flow compressor and counter-rotating relative to the radial flow compressor, and wherein the blade assembly is located axially aft of the radial flow compressor.

Compact low-pressure compressor

The present disclosure provides fluid eductors, systems that utilize fluid eductors, and methods of entraining a suction fluid flow using a fluid eductor. Exemplary fluid eductors include a concentric eductor space or a plurality of annular eductor spaces. Exemplary methods include ejecting a volume of motive fluid out of a concentric eductor space of a fluid eductor, accelerating a peripheral region of the suction fluid flow with the motive fluid ejecting out of the first annular eductor space, and accelerating a core region of the suction fluid flow with the motive fluid ejecting out of the second annular eductor space.

Fluid eductors, and systems and methods of entraining fluid using fluid eductors

A vibration isolation system for a gas turbine engine. The vibration isolation system includes a first fixed structure and a second fixed structure separate from the first fixed structure. The vibration isolation system further includes a connector coupling the first fixed structure to the second fixed structure. Additionally, the vibration isolation system includes an isolator, including a shape memory alloy material, associated with the connector. The isolator is arranged between the first fixed structure and the second fixed structure such that the isolator reduces vibrations transferred between the first fixed structure and the second fixed structure.

Shape memory alloy isolator for a gas turbine engine

A tube coupling assembly is disclosed, which comprises a first connector for connecting to a tube; a second connector for jointing with the first connector; a first member is adapted to mount on the first connector and operably affixable to the second connector; and a second member is adapted to mount on the second connector, and is capable of being engaged with the first member to prevent separation between the first connector and the second connector.

Tube coupling assembly

A turbine assembly including a first rotor assembly with a rotatable outer drum from which one or more stages of a plurality of outer drum airfoils is extended radially inward is provided. An outer casing surrounds the outer drum of the first rotor assembly. A seal assembly is coupled to the outer casing and positioned radially outward from an upstream-most stage of the plurality of outer drum airfoils. The seal assembly is positioned in axial alignment with the upstream-most stage of the plurality of outer drum airfoils. The seal assembly separates a first plenum from a second plenum. The second plenum is formed axially aft of the first plenum and is formed by the seal assembly, the outer casing, and the outer drum of the first rotor assembly. The first plenum is positioned radially outward from the upstream-most stage of the plurality of outer drum airfoils.

Flow structure for turbine engine

The present disclosure is directed generally to firewall seals for sealing pass-through members extending through a firewall, such as a firewall of a turbine engine. In one example aspect, the firewall seal includes quick-connect features that facilitate more efficient assembly and disassembly of the firewall seal to and from the pass-through member. Particularly, the firewall seal may define a slit extending through at least a portion of the seal that allows for the pass-through member to be slid through the slit and positioned in place. A retainer formed of an elastomeric material may include a metal spring plate that springs the seal back into place after the pass-through member is positioned within the seal. Moreover, a spherical bearing of the firewall seal may include features for receiving a static or dynamic pass-through member therethrough and for allowing the pass-through member to translate and rotate.

Quick connect firewall seal for firewall

A manifold for use in a clearance control system is provided. The clearance control system includes a housing including a plurality of walls that at least partially define an interior of the housing, and a nozzle portion integrally formed with the housing. The nozzle portion extends between adjacent walls of the plurality of walls and including at least one nozzle projection having a plurality of impingement openings defined therethrough. The at least one nozzle projection extends from the adjacent walls in an outward direction relative to the interior of the housing.

Manifold for use in a clearance control system and method of manufacturing

The invention relates to compound of the formula (I') in which the substituents are as defined in the specification; in free form or in salt form; to its preparation, to its use as medicament and to medicaments comprising it. 

Disubstituted heteroaryl-fused pyridines

The invention relates to compound of the formula (I), in which the substituents are as defined in the specification; in free form or in salt form; to its preparation, to its use as medicament and to medicaments comprising it. 

Diaza-spiro[5.5]undecanes

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Bengaluru, India

Vinod Shashikant Chaudhari