Carrier Corporation

United Technologies Corporation

Raytheon Technologies Corporation

William T Cousins

Vishnu Mohan Sishtla

Michael M Joly

Chaitanya Vishwajit Halbe

Thomas Gregory Tillman

Razvan Virgil Florea

Parmesh Verma

Ulf J Jonsson

Frederick James Cogswell

Larry D Burns

John D Wolter

Alberto Traverso

Xiaodan Cai

Paolo Silvestri

Carlo Alberto Niccolini

Marco Ferrando

Raffaele Spezia

David J Arend

Federico Reggio

In one embodiment, a method and a system for determining the operating state of a dynamic compressor that is mechanically connected to an electrical machine and that is equipped with a rotor that exchanges energy with a known fluid by rotating at a speed and with a driving mechanical torque, and in particular for determining the operating point of the dynamic compressor and the distance of the operating point from a surge limit curve, which delimits a stable operation zone from an unstable operation zone of the dynamic compressor.

System and method for compressor performance monitoring and surge detection

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

An exemplary compressor system includes a compressor having a fluid inlet and a fluid outlet. An isolation valve connects the fluid outlet of the compressor to a condenser. A controller is communicatively coupled to the isolation valve and the compressor. The controller includes a memory storing instructions configured to cause the controller to detect one of a surge event and a surge event precursor and restrict an opening in the isolation valve in response.

Method and system for compressor operating range extension via active valve control

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 example centrifugal compressor includes a housing that defines an inlet chamber and includes first and second openings that define a recirculation passage in fluid communication with the inlet chamber. An impeller is disposed within the housing and is rotatable about a longitudinal axis to draw fluid into the inlet chamber. The first and second openings are at different axial locations along the longitudinal axis. A plurality of inlet guide vanes are rotatable and situated in the inlet chamber. The centrifugal compressor includes a ring and a controller for moving the ring along the longitudinal axis between a first position and a second position when rotating the inlet guide vanes. The ring obstructs at least one of the first and second openings more in the second position than in the first position.

Centrifugal compressor with recirculation passage

A centrifugal compressor includes an impeller configured to drive fluid along a fluid flowpath via a plurality of discrete passages. Each of the discrete passages includes a discrete passage exit. A diffuser portion is disposed circumferentially about the impeller. The diffuser portion includes a plenum connected to each exit of the discrete passages via a plurality of diffuser inlets and an equalization plenum defined adjacent to the impeller. The equalization plenum is fluidly connected to each discrete passage exit via a corresponding slot.

Centrifugal compressor including diffuser pressure equalization feature

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 hybrid wing aircraft has an engine embedded into a body of the hybrid wing aircraft. The embedded engine has a fan that is received within a nacelle. The body of the aircraft provides a boundary layer over a circumferential portion of a fan. A system delivers additional air to correct fan stability issues raised by the boundary layer.

Embedded engines in hybrid blended wing body

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 centrifugal compressor impeller () has a hub () having a gaspath surface () extending from a leading end to a trailing end. A plurality of blades (A,B;) extend from the hub gaspath surface and each have: a leading edge (A,B;); a trailing edge (A,B;); a first face (A,B;); a second face (A,B;); and a tip (A,B;). A plurality of flow splitter segments () extend between associated twos of the blades and each spaced from both the hub gaspath surface and the tips of the associated two blades.

Centrifugal compressor open impeller

System includes a compressor having a compressor suction port and a compressor discharge port; a heat rejection heat exchanger fluidly coupled to the compressor discharge port; an expansion device fluidly coupled to an outlet of the heat rejection heat exchanger; a heat absorption heat exchanger fluidly coupled to the expansion device; a hot gas bypass line fluidly coupled to the compressor discharge port; an ejector comprising a motive port fluidly coupled to the hot gas bypass line, a suction port fluidly coupled to an outlet of the heat absorption heat exchanger and a discharge port fluidly coupled to the compressor suction port; a hot gas bypass valve positioned between the compressor discharge port and the motive port of the ejector; a flow control valve fluidly coupled to the outlet of the heat absorption heat exchanger, and fluidly coupled to the suction port of the ejector and the compressor suction port.

Growing community of inventors

Glastonbury, CT, United States of America

William T Cousins