Abstract: A fluid mover (1) includes a passage (3) of substantially constant cross section into which supersonic steam is injected through an annular nozzle (16) as a transport fluid to contact a working fluid, e.g. a liquid, to be treated, the passage further including a mixing chamber (3A) downstream of the steam injection where the mixture is accelerated upon the creation of a low pressure zone occasioned by the condensation of the steam, a dispersed droplet regime and a shock wave being generated downstream of the nozzle (16). A pseudo-convergent/divergent section is created and provides a flexible boundary in the absence of physical constraints to yield an improved performance by combining shear dispersion and/or disassociation with the effects of the shock wave. The fluid mover (1) may be used in a wide variety of applications for pumping, heating, mixing, disintegrating, classifying and separating among others.

Abstract: A fluid mover (1) includes a passage (3) of substantially constant cross section into which supersonic steam is injected through an annular nozzle (16) as a transport fluid to contact a working fluid, e.g. a liquid, to be treated, the passage further including a mixing chamber (3A) downstream of the steam injection where the mixture is accelerated upon the creation of a low pressure zone occasioned by the condensation of the steam, a dispersed droplet regime and a shock wave being generated downstream of the nozzle (16). A pseudo-convergent/divergent section is created and provides a flexible boundary in the absence of physical constraints to yield an improved performance by combining shear dispersion and/or disassociation with the effects of the shock wave. The fluid mover (1) may be used in a wide variety of applications for pumping, heating, mixing, disintegrating, classifying and separating among others.

Abstract: In a gas turbine engine power unit the gas turbine engine is provided with combustion chambers whose axes are perpendicular to the engine longitudinal axis. Each combustion chamber is located within and supported by a corresponding tubular member. Each tubular member is supported from a first annular manifold and in turn supports a second annular manifold which is located wholly within the first manifold. The first manifold receives air from the gas turbine engine compressor and directs it to a regenerative heat exchanger. Heated air returned from the regenerative heat exchanger is directed to the second manifold from where it flows through apertures in the tubular members to the combustion chambers. The manner in which the manifolds and combustion chambers are mounted reduces stresses arising from thermal gradients.

Abstract: An interturbine duct for interconnecting a gas turbine engine with a power turbine. The interturbine duct is of generally frusto-conical form and double skinned so that an annular cross-section volume is defined between the skins. Cooling air introduced in a generally tangential direction at the larger diameter extent of the duct follows a generally spiral path to the smaller diameter extent where it is exhausted into the efflux of the gas turbine engine. The spiral path of the cooling air ensures good heat transfer coefficients over both of the skins and obviates the need for baffles to direct the cooling air flow.

Abstract: A variable stator vane assembly suitable for a power turbine in which each stator vane is provided at its radially inner and outer extents with disc-shaped platforms which locate on bushes provided on associated support structure. The bushes are cooled by a flow of cooling air which is of higher pressure than that of the hot gases operationally flowing over the vanes so as to prevent the leakage of such hot gases past the bushes.