Abstract: A single-piece piston for use in a pneumatically-activated pump to meter a predetermined amount of lubricant or other liquid. The piston has a grooved end that includes a head portion and a circumferentially-disposed angled channel for containing a sealing member such as an O-ring. An adjacent stem section includes a longitudinally-disposed channel that is in fluid-flow connection with the angled channel. The piston is disposed within a chamber of the body of the pump. Lateral movement of the piston within the body causes the sealing member to shift and block and unblock the end of the longitudinal channel and an aperture in the angled channel, which allows liquid from a liquid chamber to flow into a central bore in the piston and to a pump chamber adjacent to the head of the piston's grooved end.

Abstract: A pneumatically-operated pump is provided that includes a body having a central bore with a liquid chamber for a slidable piston injector, a chamber for a removable reservoir, and an inlet and outlet for a gas. A priming conduit carries liquid from the reservoir mounted on the body to the injector in the liquid chamber which injects the liquid into a liquid line coupled to a fitting on the pump. The liquid line carries lubricant or other liquid from the pump (e.g., air tool lubricator) to an air tool or other article. A priming pump is mounted on the body and is capable of delivering a predetermined amount of liquid from the reservoir to the liquid chamber. The priming pump is used to fill the liquid line with liquid.

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.