General Electric Company

Dominion Engineering Works, Limited

David Graham Holmes

Douglas Carl Hofer

Zachary William Nagel

Anthony John Dean

Anil Gulati

Eayre Bruce Voorhees

Richard A Novak

Jacques Y McNabb

Ravindra Gopaldas Devi

The present invention provides novel supersonic compressors comprising novel supersonic compressor rotors. The supersonic compressor rotors are designed to operate at very high rotational speed wherein the velocity of the gas entering the supersonic compressor rotor is greater than the local speed of sound in the gas, hence the descriptor 'supersonic'. The new supersonic compressors comprise at least one supersonic compressor rotor defining an inner cylindrical cavity and an outer rotor rim and at least one radial flow channel allowing fluid communication between the inner cylindrical cavity and the outer rotor rim, said radial flow channel comprising a supersonic compression ramp. The novel supersonic compressor rotors are expected to enhance the performance of supersonic compressors comprising them, and to provide for greater design versatility in systems comprising such novel supersonic compressors.

Supersonic compressor comprising radial flow path

A supersonic compressor rotor. The supersonic compressor rotor includes a rotor disk that includes an upstream surface, a downstream surface, and a radially outer surface that extends generally axially between the upstream surface and the downstream surface. The radially outer surface includes an inlet surface, an outlet surface, and a transition surface that extends between the inlet surface and the outlet surface. A plurality of vanes are coupled to the radially outer surface. Adjacent vanes form a pair and are oriented such that a flow channel is defined between each pair of adjacent vanes. The flow channel extends between an inlet opening and an outlet opening. The inlet surface defines an inlet plane that extends between the inlet opening and the transition surface. The outlet surface defines an outlet plane that extends between the outlet opening and the transition surface that is not parallel to the inlet plane. At least one supersonic compression ramp is positioned within the flow channel to facilitate forming at least one compression wave within the flow channel.

Supersonic compressor rotor and method of assembling same

A novel supersonic compressor is provided by the present invention. In one embodiment, the novel supersonic compressor comprises a fluid inlet, a fluid outlet, and at least two counter rotary supersonic compressor rotors, said supersonic compressor rotors being configured in series such that an output from a first supersonic compressor rotor having a first direction of rotation is directed to a second supersonic compressor rotor configured to counter-rotate with respect to the first supersonic compressor rotor.

Supersonic compressor

Ruler

Shower valve

Combustion-induced instabilities are minimized in gas turbine combustors by incorporating one or more Helmholtz resonators into the combustor. First and second plates located in the head end of the combustor casing define one cavity, and a sleeve located between the casing and the liner defines another cavity. Each of the two cavities is connected to the combustion chamber by one or more throats, thus forming Helmholtz resonators. The throats of each resonator can be tubes of different lengths and/or different cross-sectional areas to provide dynamics suppression over a broad band of frequencies. The throats can also be arranged such that each throat is associated with a different portion of its respective cavity, each cavity portion having a different volume.

Dynamics free low emissions gas turbine combustor

An improved Francis-type turbine runner permitting a significant reduction in cavitation is provided by shaping the runners extending between the ring and crown in such a fashion that at least a portion of the area of the streamlined suction face side of each blade is (when used as a turbine) exposed when viewed in the axial direction looking away from the crown.

Blade configurations for Francis-type turbine runners

A tuned sound barrier for machines which radiate sound primarily at a few constant, discrete frequencies includes an array of mechanical resonators distributed over the surface of a sound barrier. Each resonator of the array is tuned to present a high mechanical impedance to transmission of mechanical vibration at one of the discrete frequencies emitted by the source machine. The tuned sound barrier may be either a free-standing sound barrier or an attachment to a housing for the machine.

Growing community of inventors

Schenectady, NY, United States of America

David Graham Holmes