To contain high energy fragments generated by a hub burst, a compressor containment assembly in a gas turbine engine includes a diffuser housing having an arcuate portion that defines a channel which traps the high energy fragments and an axial facing U-shaped which imparts flexibility. The assembly also includes a concave back shroud having a series of grooves that create resistance for the fragments as they slide along its surface. At its radial outer end the back shroud has an annular rim that absorbs some of the energy and delays the shearing of bolts. A bumper is disposed between the back shroud and a turbine wheel to limit the deflection of the back shroud during a hub burst.

Centrifugal compressor hub containment assembly

Fluid pumping apparatus comprises (a) a housing, (b) an impeller rotatable in the housing to discharge fluid centrifugally outwardly, (c) a rotary spool having an inducer section through which intake fluid passes to the impeller, (d) a rotary diffuser associated with the rotary spool and having driving vanes located at the inlet of the diffuser and outwardly of the impeller periphery for rotatably driving the spool in response to outward flow of said discharged fluid against and between the vanes.

Free spool inducer pump

A centrifugal compressor having a two section diffuser (41) which has a tapered section (47) having a constant diffusing area along its radial length, and a straight section (46) having an increasing diffusing area along its radial length, and a diffusing volute (45) having a throat area (54) significantly larger than conventional designs.

Centrifugal compressor having hybrid diffuser and excess area diffusing volute

A gas compressor based on the use of a driven rotor having a compression ramp traveling at a local supersonic inlet velocity (based on the combination of inlet gas velocity and tangential speed of the ramp) which compresses inlet gas against a stationary sidewall. In using this method to compress inlet gas, the supersonic compressor efficiently achieves high compression ratios while utilizing a compact, stabilized gasdynamic flow path. Operated at supersonic speeds, the inlet stabilizes an oblique/normal shock system in the gasdyanamic flow path formed between the rim of the rotor, the strakes, and a stationary external housing. Part load efficiency is enhanced by the use of a pre-swirl compressor, and using a bypass stream to bleed a portion of the intermediate pressure gas after passing through the pre-swirl compressor back to the inlet of the pre-swirl compressor. Inlet guide vanes to the compression ramp enhance overall efficiency.

Supersonic gas compressor

The present invention is an improvement in radial diffusers employed in a turbine engine having a centrifugal compressor The walls of the diffuser define at least one flow passage through the diffuser having a first portion with a first cross-sectional area and a second portion having a larger, second cross-sectional area The first wall section is spaced apart from the second wall section so as to define a bleed aperture therebetween A vortex fence extends outwardly from the wall surface at the leading edge of the second wall portion Preferably, the bleed aperture and the vortex fence are disposed on the suction surface of each vane in a vaned radial diffuser

Vortex controlled radial diffuser for centrifugal compressor

A diffuser for use in turbomachinery to improve overall efficiency, the diffuser including a vaneless diffuser section for reducing supersonic fluid flow to subsonic speed and a multichannel diffuser section for achieving maximum pressure recovery and delivering the fluid to a suitable collector, one of the diffuser sections providing a flow path of decreasing and then increasing cross section configured to minimize boundary layer losses.

Shao L Soo

Papers

Diffuser including vaneless and vaned sections