General Electric Company

Intel Corporation

Arnab Sen

Jeffrey Douglas Rambo

Bhaskar Nanda Mondal

Jeff Ku

Nathan Evan McCurdy Gibson

Arvind Namadevan

Robert Proctor

Prakash Kurma Raju

Rajesh Kumar

Juha Paavola

Hari Shanker Thakur

Brandon Wayne Miller

Daniel Alan Niergarth

Christopher Charles Glynn

Alan Roy Stuart

Gavin Sung

Justin Michael Huttula

Lance Lin

Jason Y Jiang

Christopher Jon Potokar

Evan Piotr Kuklinski

Kishanjit Pal

Gerry Juan

Hariharan Manickavasagam Sarojini

Bikramjit Chatterjee

Min Suet Lim

Steven Douglas Johnson

Mark Charles Carbone

Shantanu Dattatraya Kulkarni

Vivek Paranjape

Prasanna Pichumani

Weize Kang

Daniel J Ragland

Gustavo Fricke

Pranav R Kamat

Tim Liu

Bijendra Singh

Hua Yang

Kannan G Raja

Gokul V Subramaniam

Kathiravan D

Baomin Liu

Shankar Jayaraman

Xiyong Tian

Tongyan Zhai

Ruander Cardenas

Jia Yan Go

Twan Sing Loo

Columbia Mishra

Christopher M Moore

Keith Blodgett

Ritu Bawa

Mohamed Musthafa Thoppil

Mark Macdonald

Vijith Halestoph R

Javed Shaikh

Chin Kung Goh

Avinash Manu Aravindan

Siddhartha Pal

Khal Ern See

Sammi Wy Liu

Nehakausar Pinjari

Mikko Makinen

A Ezekiel Poulose

Isha Garg

Wan Yu Liu

Cora Nien

Mayur Ghawat

Chun-Ting Liu

Shih Wei Nien

George Baoci Sun

Hari Shankar Thakur

Computer with extendable monitor

Systems, apparatus, articles of manufacture, and methods are disclosed for accessories for electronic devices and removable fan cartridges for electronic devices. An example electronic device accessory includes a backplate panel removably couplable to a first chassis of a first electronic device to replace a portion of a first cover of the first chassis and removably couplable to a second chassis of a second electronic device to replace a portion of a second cover of the second chassis. The example electronic device accessory also includes a mating device to releasably couple the backplate panel to the first chassis and independently releasably couple the backplate panel to the second chassis and a fan coupled to the backplate panel. The fan is to increase a Z height of the first electronic device when the backplate panel is coupled to the first electronic device and increase a Z height of the second electronic device when the backplate panel is coupled to the second electronic device.

Removable fan cartridges for electronic devices

An electronic device comprises a heat source and a heat distribution structure coupled to the heat source to distribute heat generated by the heat source during operation of the electronic device.

Cooling systems, cooling structures and electronic devices and methods for manufacturing or operating cooling systems, cooling structures and electronic devices

There is disclosed in one example a heat dissipator for an electronic apparatus, including: a planar vapor chamber having a substantially rectangular form factor, wherein a second dimension dof the rectangular form factor is at least approximately twice a first dimension dof the rectangular form factor; a first fan and second fan; and a first heat pipe and second heat pipe discrete from the planar vapor chamber and disposed along first and second dedges of the planar vapor chamber, further disposed to conduct heat from the first and second dedges to the first and second fan respectively.

Vapor chambers

An aspirating face seal between high and low pressure regions of a turbomachine at a juncture between rotatable and non-rotatable members of turbomachine includes gas bearing rotatable and non-rotatable face surfaces. Primary and starter seal teeth and optional deflector seal tooth are mounted on seal teeth carrier on rotatable member. Non-rotatable face surface is mounted on an annular slider on the non-rotatable member. A pull-off biasing means urges the annular slider away from the rotatable member and the non-rotatable face surface away from the rotatable surface. A secondary seal is in sealing engagement with the annular slider in the low pressure region and the pull-off biasing means is located radially outwardly of the annular slider in the high pressure region. Biasing means may include coil springs within spring chambers of circumferentially spaced cartridges. Tongues extend inwardly from spring chambers into grooves in slider.

Anti-coning aspirating face seal

An aspect of the present disclosure is directed to a system for reducing thermal gradient at a heat engine. The heat engine includes a rotor assembly with a rotor disk and a seal assembly is provided. An interfacing structure at least partially surrounds the rotor assembly at the seal assembly. The seal assembly and the interfacing structure together form a first cavity defining a first environmental condition and a second cavity defining a second environmental condition. A fluid supply manifold is connected to the rotor assembly and is extended at least partially along a radial direction from the first cavity to an outlet opening in thermal communication with the rotor disk of the rotor assembly.

System for rotor assembly thermal gradient reduction

An ejector assembly includes a primary nozzle in fluid communication with a primary fluid inlet, a secondary nozzle in fluid communication with a secondary fluid inlet, the primary nozzle being oriented concentrically within the secondary nozzle and the secondary nozzle having a venturi downstream of the primary nozzle, and the primary nozzle having a variable cross-sectional area. A gas turbine engine includes a source of high pressure air, a region of low pressure air, and an ejector assembly, the ejector assembly includes a primary nozzle in fluid communication with a primary fluid inlet, the primary fluid inlet in fluid communication with the source of high pressure air, a secondary nozzle in fluid communication with a secondary fluid inlet, the secondary fluid inlet in fluid communication with the region of low pressure air, the primary nozzle being oriented concentrically within the secondary nozzle and the secondary nozzle having a venturi downstream of the primary nozzle, and the primary nozzle having a variable cross-sectional area.

Variable area ejector

An apparatus for a turbine engine comprising an outer casing, an engine core provided within outer casing and having a at least one set of blades, and through which gasses flow in a forward to aft direction, an outer drum located within the outer casing to define an annular cavity. A set of seals extending between the first surface and the second surface to define at least one cooled cavity within the annular cavity.

Turbine engine with annular cavity

An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft includes a fuselage extending longitudinally between the forward end of the aircraft and the aft end of the aircraft; a primary wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; a first engine mounted to the primary wing assembly; and a first engine wing assembly extending outward from the first engine.

Aircraft having an engine wing assembly

A method of operating a thermal management system for a gas turbine engine includes determining the gas turbine engine is in a first operating mode; transferring heat from a first heat source exchanger to a heat sink system in response to determining the gas turbine engine is in the first operation mode, the first heat source exchanger thermally coupled to a first system/component of the gas turbine engine; determining the gas turbine engine is in a second operating mode, the second operating mode being different than the first operating mode; and transferring heat from a second heat source exchanger to the heat sink system in response to determining the gas turbine engine is in the second operation mode, the second heat source exchanger thermally coupled to a second system/component of the gas turbine engine, the second system/component being different than the first system/component.

Thermal management system

The present disclosure is directed to a system for mitigating rotor bow at a turbine engine. The system includes a casing circumferentially surrounding a rotor assembly in which a heat pipe is attached to the casing and extended circumferentially around the rotor assembly.

Heat pipe in turbine engine

Particular embodiments described herein provide for an electronic device that includes a hybrid keyboard. The keyboard can include a first portion of keys with a first key travel and a second portion of keys with a second key travel. The second key travel is less than the first key travel and a support plate can be raised under the second portion of keys and cause the second portion of keys to have the second key travel. In an example, a heat pipe or some other component can be located under the raised support plate and second portion of keys with the second key travel.

Hybrid keyboard

An aeronautical gas turbine engine includes a turbomachine including a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order. The aeronautical gas turbine engine additionally includes a closed cycle heat engine including a compressor configured to compress a working fluid; a primary heat exchanger in thermal communication with the turbomachine and the working fluid, the primary heat exchanger configured to transfer heat from the turbomachine to the working fluid; an expander coupled to the compressor for expanding the working fluid; and an output shaft driven by the expander.

Closed cycle heat engine for a gas turbine engine

A turbine engine with a stator having axially spaced first and second structural elements along with a rotor and a face seal between the rotor and the stator including a non-rotating gas bearing face coupled to the first and second structural elements, and a rotating gas bearing face coupled to the rotor and confronting the non-rotating gas bearing surface. Introducing airflow to one or multiple parts of the seal.

Engine with face seal

Growing community of inventors

Bengaluru, India

Arnab Sen