General Electric Company

Nuovo Pignone Srl

Nuovo Pignone Spa

Nuovo Pignone Tecnologie Srl

Ge Oil & Gas Esp, Inc.

Thermodyn

Vittorio Michelassi

Siddharth Navinchandra Ashar

Ismail Hakki Sezal

Douglas Carl Hofer

Jeremy Daniel Van Dam

Rodrigo Rodriguez Erdmenger

Rene Du Cauze De Nazelle

Manoj Ramprasad Shah

Christof Martin Sihler

Simon Herbert Schramm

Ramakrishna Venkata Mallina

Ivan Malcevic

Christopher Edward Wolfe

Mohamed Osama

Farshad Ghasripoor

Christian Aalburg

Daniel Edward Loringer

Sebastian Walter Freund

Andreas Herrig

Nathan Evan McCurdy Gibson

Giuseppe Sassanelli

Matthew Alexander Lehar

Giridhar Jothiprasad

Massimo Giannozzi

Svend Erik Rocke

Sungho Yoon

Roderick Mark Lusted

Lorenzo Bergamini

John David Stampfli

Michael Franklin Hughes

Xuele Qi

Rudolf Konrad Selmeier

Matthias Finkenrath

Quang Tue Nguyen Tran

Antonio Guijarro Valencia

Egidio Marotta

Davide Giacché

Vishal Gahlot

Rosa Castane Selga

Stefano Francini

Alexander Kimberley Simpson

Rajesh Kumar Venkata Gadamsetty

Ajay Keshava Rao

Sean Craig Jenkins

Nuo Sheng

Erik Mele

Guillaume Becquin

Christian Vogel

Cathal Clancy

Chaitanya Venkata Rama Krishna Ongole

Scott Richard Erler

Haris Ligata

Carsten Michael Schneider

Sylvain Guillemin

Scott Alan Harban

Ilia Oxman

Ravishankar Balasubramanian

Nathaniel David Varano

Brent David Michalowski

Kenton Travis Shonhor

Rene De Nazelle

René Du Cauze De Nazelle

Miguel Angel Gonzalez

Lacopo Giovannetti

Dennis M Gray

Roderick Lusted

A compressed air energy storage system is described, including a compressor fluidly coupled to a compressed air reservoir and an expansion train including at least a first turbine. The system further includes an electric machine aggregate configured: for converting electric power into mechanical power and driving the compressor therewith during the energy storing mode; and for converting mechanical power produced by the expansion train into electric power during the power production mode. A combustor is configured for receiving fuel and compressed air and producing combustion gas, and for supplying the combustion gas to the first turbine.

Constant flow function air expansion train with combuster

A liquid ring fluid flow machine is presented. The machine includes a stationary annular housing having an outer surface and an inner surface. The inner surface defines a chamber that is arranged to receive a liquid. A rotor having a core and a plurality of radially extending vanes is eccentrically rotatably mounted within the chamber for directing the liquid into a recirculating liquid ring in proximity to the inner surface of the housing within the chamber. The inner surface of the housing that is in contact with the recirculating liquid ring is covered by a hydrophobic coating. The machine further includes a first supply pipe and a second supply pipe, each in fluid communication with the chamber.

Liquid ring fluid flow machine

A fluid processor for use in a downhole pumping operation includes a fluid processing stag, a nozzle stage and a gas compressor stage. The nozzle chamber is configured as a convergent-divergent nozzle and the variable metering member is configured for axial displacement within the convergent section to adjust the open cross-sectional area of the nozzle. A method for producing fluid hydrocarbons from a subterranean wellbore with a pumping system includes the steps of measuring a first gas-to-liquid ratio of the fluid hydrocarbons and operating a motor within the pumping system to operate at a first rotational speed. The method continues with the steps of measuring a second gas-to-liquid ration of the fluid hydrocarbons with the sensor module, where the second gas-to-liquid ratio is greater than the first gas-to-liquid ratio, and operating the motor at a second rotational speed that is faster than the first rotational speed.

Downhole wet gas compressor processor

A multistage centrifugal compressor is described. The compressor comprises a casing and a shaft rotatingly supported in the casing by at least a first bearing and a second bearing. At least one in-between-bearing impeller is mounted on the shaft, between the first bearing and the second bearing. An overhung impeller is mounted at one end of the shaft. A first diaphragm arrangement is further located in the casing. The first diaphragm arrangement comprises return a channel assembly with a plurality of stationary return channel blades defining a plurality of return vanes for redirecting compressed gas from an exit location of the overhung impeller to an inlet location of the in-between-bearings impeller. The first diaphragm arrangement houses one of the first bearing and second bearing.

Multistage centrifugal compressor

A compressor is provided including a compressor end-wall having a casing and a hub. The compressor further includes at least one set of rotor blades, one set of stator blades, and a plurality of end-wall treatments spaced apart from each other, formed in an interior surface of at least one of the casing and hub, and facing a tip of the rotor blade or stator blade. Each end-wall treatment includes a forward recess portion extending along a first axis and an aft recess portion extending along a second axis different than the first axis. The aft recess portion is joined to the corresponding forward recess portion via an intersection portion which is inclined relative to at least one of the first axis, and the second axis. The aft recess portion and/or the forward recess portion are bent from the intersection portion and inclined relative to an axial direction of the compressor.

Compressor end-wall treatment having a bent profile

An apparatus and method are disclosed for a gas turbine engine including an offtake located within the air flow of the engine. The offtake has an inlet and a louver covering the inlet. The louver has multiple airfoils arranged to direct the air flow into the inlet of the offtake.

Gas turbine engine with an offtake

A rotating machinery equipment is disclosed, including a rotating electrical machine having a stator () and a rotating shaft (), whereon a rotor () is mounted. The machinery equipment further includes a cooling fan () comprised of a rotating impeller () mounted on the rotating shaft () for co-rotation therewith. Cooling gas passages () are provided for delivering compressed cooling gas through the stator and rotor. The cooling gas is delivered by the impeller () into a cooling-gas distribution chamber (). The pressure of the cooling gas in the cooling-gas distribution chamber generates an axial force balancing the axial thrust generated on the electrical machine by the cooling gas flow.

Fan-cooled electrical machine with axial thrust compensation

An electric pump powered by an electric motor having a stator disposed within a hollow rotor is provided. Impellers on the rotor outer surface extend into a fluid flow path defined by the pump. One or more torque-producing rotor sections are driven by a plurality of independently controllable stator sections disposed within the rotor cavity. The relative positions of the rotor and stator are maintained by a plurality of bearings configured to allow rotation of the rotor and defining a bearing span. The pump is configured such that the stator and rotor share the same bearing span. Such an arrangement reduces motor windage losses relative to conventional motors in which the rotor is disposed within the stator, owing to a reduction in the diameter of the air gap between the stator and the rotor. In addition, the peripheral speed of the pump is increased owing to an increase in the rotor diameter.

Integrated motor and fluid pump

Centrifugal compressor having flow-control blades in which each of the flow-control blades has a pressure side and an opposite suction side. Each of the flow-control blades includes a main section and an inducer section that project away from an impeller surface. The inducer section is positioned upstream from the main section. The inducer section includes a trailing edge and the main section includes a leading edge that is spaced apart from the trailing edge. The inducer sections are aligned with the respective main sections as the inducer and main sections project from the impeller surface to a designated point above the impeller surface. Each of the trailing edges of the inducer sections and the respective leading edge of the main section form a bleed gap therebetween after the designated point. The bleed gap is configured to permit fluid to flow therethrough from the pressure side to the suction side.

Centrifugal compressor and system

A compressor for a gas turbine engine including one or more endwall treatments for controlling leakage flow and circumferential flow non-uniformities in the compressor. The compressor includes a casing, a hub, a flow path formed between the casing and the hub, a plurality of blades positioned in the flow path, and one or more circumferentially varying end-wall treatments formed in an interior surface of at least one of the casing or the hub. Each of the one or more circumferentially varying endwall treatments circumferentially varying based on their relative position to an immediately adjacent upstream bladerow. Each of the one or more endwall treatments is circumferentially varied in at least one of placement relative to the immediately adjacent upstream bladerow or in geometric parameters defining each of the plurality of circumferentially varying endwall treatments. Additionally disclosed is an engine including the compressor.

Circumferentially varying axial compressor endwall treatment for controlling leakage flow therein

A subsea boosting module for use with an alternating current (AC) power system includes a housing defining at least one interior chamber. A fluid pump is disposed within the interior chamber. An electric motor is disposed within the interior chamber and drivingly coupled to the fluid pump. A plurality of power components is disposed within the interior chamber to deliver power to the electric motor.

Methods and systems for subsea boosting with direct current and alternating current power systems

Three-dimensional (3D) return vane for a multistage centrifugal compressor. The return channel vane extends upstream to a region proximate the bend apex of the return channel. In each point of the return channel vane, the angle 'beta' is defined as the acute angle between the tangent to the local camberline and the local circumferential direction. At each normalized position between leading edge and trailing edge, the local twist of the return channel vane is defined as the algebraic difference between the angles beta at the two points at hub and shroud having said normalized position. When moving in streamwise direction from leading edge to trailing edge, the twist first decreases, reaching an algebraic minimum, then increases, reaching an algebraic maximum, then decreases again. However, the absolute twist of the algebraic minimum is larger than the absolute twist of the algebraic maximum.

Centrifugal compressor with twisted return channel vane

Gas bearing for an aspirating seal assembly is disclosed. The gas bearing includes a bearing body having a bearing surface. The gas bearing further includes a first through-hole disposed in the bearing body, and a plurality of second through-holes spaced apart from each other and disposed around the first through-hole. The first through-hole is characterized by a size, and a first central axis. Each second through-hole is characterized by a size, and a second central axis. The second central axis of each second through-hole in the plurality of second through-holes intersects the first central axis at an angle in a range from about 30 degrees to about 150 degrees or at an angle in a range from about &#x2212;30 degrees to about &#x2212;150 degrees. Size of at least one through-hole in the plurality of second through-holes is different from the size of the first through-hole.

Gas bearing and an associated method thereof

A flow angle probe is provided comprising: (a) a probe vane configured to contact a moving fluid within a fluid conduit; (b) an optional probe mounting mechanically coupled to the probe vane; (c) a rotary shaft coupled either to the optional probe mounting or the probe vane; (d) a rotary encoder coupled to the rotary shaft; (e) a sensor hermetically isolated from the probe vane and configured to sense a change in position of the rotary encoder; and (f) a probe housing encompassing at least a portion of the rotary shaft, the rotary encoder and the sensor. The novel flow angle probes disclosed herein may be used in a wide variety of turbomachines and fluid processing systems, and applications, including turbomachine design and operational control, as well as in flow assurance.

Flow angle probe with a passively rotating vane

An impeller designed to be mounted on a rotary shaft includes: a basic rim provided with blades protruding on one surface of the basic rim, and a hub capable of being coupled to the basic rim and to the rotary shaft. In certain embodiments, the impeller includes an annular plate and the hub, where the annular plate and the basic rim are configured to interact together so as to hold the basic rim axially and to maintain a freedom of radial deformation of the basic rim relative to the hub and to the annular plate.

Radial impeller with a radially free basic rim

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Munich, Germany

Vittorio Michelassi