United Technologies Corporation

Hamilton Sundstrand Corporation

Raytheon Technologies Corporation

Benjamin E Fishler

Loc Quang Duong

Xiaolan Hu

Jay Francisco

Jesus A Garcia

Nagamany Thayalakhandan

Gao Yang

Gregory G Johnson

Dan G Sapiro

Ralph E Gordon

Steven R Falconer

Ulrike Kaul

Jay M Francisco

The present disclosure relates generally a gas turbine engine and a rotor therefor. The rotor may include a symmetric rim thereon to prevent the propagation of induced vibratory responses. The rim may have one or more sloping surfaces to prevent the re-attachment of boundary layer flow.

Rotor and gas turbine engine including a rotor

A turbo-machine inlet includes a gas passage having a non-gradual bend prior to an impeller assembly. The non-gradual bend causes a localized shockwave in fluid flowing through the gas passage.

Method and apparatus for turbo-machine noise suppression

The presently disclosed embodiments utilize flow from a higher-energy portion of flow within the impeller flow path and inject it into the lower-energy portion of the flow path to re-energize the flow, delaying the onset of, or minimizing, large (and inefficient, entropy-generating) re-circulation zones in the flow field. By making a spanwise cut along the chord length of the splitter blade (variable blade clearance from leading edge to trailing edge), additional secondary flow occurs within the flow passages as the higher pressure flow on the pressure side of the blade can now spill over into the low-pressure suction side of the blade.

Variable span splitter blade

A reduction in excitation amplitudes affecting turbine blade durability in a turbine nozzle assembly having a plurality of vanes and turbine blades, includes: identifying a turbine blade design of the turbine nozzle assembly; performing a modal model analysis of at least one of the turbine blades in the turbine blade design; reducing aerodynamic impact by ensuring that each of the turbine blades is free of aero-excitation from an upstream flow at the vanes in an operating speed range; identifying blade natural frequencies with respect to the nozzle vanes; and modifying a trailing edge of at least one of the vanes to reduce the excitation amplitudes.

Reduction of equally spaced turbine nozzle vane excitation

The present disclosure relates to shroud bleed in centrifugal compressors. An air-limiting componentmay be located adjacent to a shroud. The shroudmay have a primary bleed slot, and the air-limiting componentmay have a secondary bleed slot. The primary bleed slotand the secondary bleed slotmay overlap at an effective bleed slot location. The air-limiting componentmay rotate relative to the shroud, which may change a streamwise location of the effective bleed slot.

Variable bleed slot in centrifugal impeller

An assembly for reducing compressor noise includes a compressor and an acoustic shield. The compressor has a rotor with a plurality of blades mounted thereto. Additionally, the compressor has one or more bleed slots therein. The acoustic shield is disposed adjacent to the one more bleed slots and spaced at a distance therefrom.

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San Diego, CA, United States of America

Benjamin E Fishler