Abstract: An air purification system for a vehicle may comprise a first heated-ambient-air source comprising an engine with an ambient air compressor; and at least one heated-ambient-air outlet. The system may also comprise a second heated-ambient-air source; a mixing valve; a first heated-ambient-air channel connected between the at least one heated-ambient-air outlet of the engine and the mixing valve; a second heated-ambient-air channel connected between the second heated-ambient-air source and the mixing valve; and a catalytic decontamination unit positioned between the mixing valve and an enclosed passenger cabin of the vehicle for removing contaminants from ambient air and producing decontaminated air to the enclosed passenger cabin.

Abstract: The present invention is directed to a fluidic system and method for controlling the airflow to a lean premix combustor. The system and method as disclosed allow for reduced power, which results in reduced emissions, while at the same time providing excellent performance. This is accomplished through the use of fluidic means, which do not have the problems associated with hot moving parts of prior art mechanical means. Specifically, the introduction of an airflow downstream from openings in the dilution section cause a local boundary layer separation forcing air into the dilution holes.

Abstract: The present invention is directed to a fluidic system and method for controlling the airflow to a lean premix combustor. The system and method as disclosed allow for reduced power, which results in reduced emissions, while at the same time providing excellent performance. This is accomplished through the use of fluidic means, which do not have the problems associated with hot moving parts of prior art mechanical means. Specifically, the introduction of an airflow downstream from openings in the dilution section cause a local boundary layer separation forcing air into the dilution holes.

Abstract: A gas turbine engine includes, in flow series arrangement, a mixer, a compressor, a first flow path of a recuperator, a combustor, a turbine and a second flow path of said recuperator; and a bypass conduit between said turbine and said mixer. A valve is disposed in the conduit and is controlled by a temperature sensor mounted to sense compressor inlet air temperature. The sensor has a set point temperature that corresponds with optimum emissions from the engine. When the sensed temperature drops below the set point temperature the valve opens and hot air from the turbine flows to the mixer where it heats the air entering the compressor. A method for operating a gas turbine engine with preselected emissions over a range of ambient conditions is also disclosed.

Abstract: A power generating system, including a first shaft, a first compressor, a second compressor and a turbine. In a further embodiment, the system also includes a second turbine, a second shaft and a generator. Each of the first compressor, the second compressor and the turbine are connected to the first shaft whereby the first shaft, the first compressor, the second compressor and the turbine all rotate at the same speed. The first compressor and second compressor are of disparate flow types.

Abstract: A secondary power generating system and method is provided that can drive an aircraft's accessories, and deliver cooling flow and fuel flow to a propulsion engine such as a turbojet, ramjet or turboramjet. This system and method employs a heat exchanger in which high pressure, endothermic, liquid fuel absorbs heat from the air exiting the engine's compressor and as a result is transformed into a high pressure, gaseous fuel. The high pressure gas is expanded across a motor which extracts the pressure energy and converts this energy into mechanical power for driving accessories. The gas is then fed into the engine's combustor where it is ignited. The cooled air exiting the heat exchanger is returned to the propulsion engine and is used for cooling various components such as blades and shafts therein.

Abstract: An annular seal apparatus of the labyrinth type includes at least a pair of axially stacked thin diaphragm members. Each of diaphragm members includes a planar array of radially and circumferentially extending fingers separated by gaps. The pair of diaphragm members are disposed so that the fingers of each block the gaps of the other to define an axially extending annular labyrinth.

Abstract: An annular seal apparatus of the labyrinth type includes at least a pair of axially stacked thin diaphragm members. Each of diaphragm members includes a planar array of radially and circumferentially extending fingers separated by gaps. The pair of diaphragm members are disposed so that the fingers of each block the gaps of the other to define an axially extending annular labyrinth.

Abstract: A high performance turbine engine includes refrigeration apparatus powered by the engine and effective upon a fractional air flow received from the engine compressor to provide chilled air for cooling of internal engine components. The refrigeration process facilitates rejection of unwanted heat to ambient air despite high stagnation temperatures at high flight speeds. The invention allows increased turbine inlet temperature and improved fuel efficiency or thrust per pound of engine weight with present-day metals and cooling technology being used for engine construction.

Abstract: A composite member includes circumferentially extending ceramic fibers in a metallic matrix. A rotor member integrally includes such a ceramic fiber/metal matrix composite member to reinforce a homogeneous remainder portion of the rotor member with respect to centrifugally induced stresses. Method of making are included in the disclosure.

Abstract: A composite member includes circumferentially extending ceramic fibers in a metallic matrix. A rotor member integrally includes such a ceramic fiber/metal matrix composite member to reinforce a homogeneous remainder portion of the rotor member with respect to centrifugally induced stresses. Method of making are included in the disclosure.

Abstract: A rotor member for a turbomachine includes a first portion formed of comparatively higher creep rupture strength material, and a second portion integrally joined to the first portion and formed of comparatively higher tensile strength material. The rotor defines a bore and is configured such that the operative environment thereof inflicts higher temperatures upon the first portion, and higher centrifugally-induced stresses upon the second portion. In order to improve the operating speed, burst margin, or both, of the rotor a plurality of circumferentially spaced and annularly arrayed cavities are provided within the rotor at the union of the two portions. The portions are intimately united by hot isostatic pressing (HIP) so that the rotor is of a single piece (monolithic) having portions of selected physical properties appropriate to the thermal/physical stresses imposed thereon, and defining voids which reduce the weight and bore stresses thereof.

Abstract: Method and apparatus for delivering cooling fluid flow to the internal blade cooling passages in a gas turbine engine, wherein cooling flow is injected into a radial side face of the hub of the turbine wheel and is ported therefrom through internal passages in the hub to the blade internal cooling passages.

Abstract: A cantilevered bearing damper assembly has an elastomeric camping section which is maintained essentially entirely in a shear stress condition during lateral deflection of an annular bearing secured to the assembly.