Abstract: A combustion structure for a turbine engine includes an annular combustion cavity into which flows a part of each of a plurality of radially outwardly flowing primary air jets to define a rotating toroid of primary combustion air. Plural annular louvers defined in the walls of the combustion cavity provide plural film-like wall cooling air flows moving in agreement with the rotating toroid of primary combustion air. An annular array of circumferentially spaced apart and disposed louvers in a radially outer wall of the combustor structure provide film-like air flows to energize the rotating toroid of combustion air to swirl about the combustion cavity.

Abstract: An annular sealing apparatus comprised of at least a pair of axially stacked thin diaphragm members is provided. Each of diaphragm members includes a planar array of radially extending fingers separated by gaps. The fingers have a logarithmic curvature as they extend from their innermost end to their outermost end. The fingers also have a constant thickness along their length and also have a foot integral with their innermost end. This foot is wider than the fingers and thereby provides a larger wear surface. The pair of diaphragm members are disposed so that the fingers of each block the gaps of the other.

Abstract: A single crystal turbine blade has a portion of its attachment section reinforced by a core containing a fine grained, polycrystalline alloy. The blade is prepared by casting a single crystal body with a cavity within the attachment section, and then filling the attachment section with the polycrystalline superalloy to form a composite structure. Filling is preferably accomplished by plasma spraying the cavity with the superalloy, and hot isostatically compacting the sprayed superalloy to minimize porosity. The composite structure is then heat treated to develop an optimized microstructure in the dual alloy attachment section. The resulting turbine blade has improved low cycle fatigue life of the composite attachment section.

Abstract: A flow modulator (48) for a butterfly valve (40) incorporates a first protrusion (64) on the high-pressure side (52) of the modulator and a second protrusion (66) on the low-pressure side (54). The second protrusion (66) is spaced from the leading edge (60) to define a surface portion (88) of the low-pressure side (54). In operation, the second protrusion (66) functions as a flow restrictor that increases pressure in a region (86) of the flow path (44) bordered in part by the second protrusion and the surface portion (88). This increase in pressure serves to minimize the net aerodynamically-induced closing torque exerted on the modulator (46). The height of the second protrusion and its distance from the leading edge are shown to be important design parameters. In addition, the use of a third protrusion (114) for reducing torque drop-off at high rotational angles is disclosed.

Abstract: Apparatus for cooling pliant film bearings of turbomachinery or the like and for protecting such bearings against heat transfer from the turbine side of the machinery. The turbomachine incorporates a hollow shaft for better cooling. Embodiments of the invention circulate cooling air through the interior of the hollow shaft and provide various structural configurations to thermally isolate the bearing shaft from the turbine wheel.

Abstract: A method for facilitating control of a butterfly valve, butterfly valves (40, 180) adapted for use with the method, and a fluid system (242) incorporating such valves are disclosed. All three use or incorporate butterfly valve structure that provides for relative translational movement (246) between the valve plate (42, 182, 248) and a pivot axis (232) in order to alter fluid dynamic torque exerted on the valve plate.

Abstract: A radial inflow rotor for a gas turbine engine has a dual structure for improving the low cycle fatigue life of the saddle region. The interior core or hub of the rotor is a high strength polycrystalline alloy while a series of outer blade segments is individually cast as single crystals and bonded so that their low modulus (100) crystallographic axis is aligned substantially tangential to the rotor's circumference at the saddle.

Abstract: A marine acoustic detector for use in identifying a characteristic airborne sound pressure field generated by a propeller-driven aircraft including a surface-buoyed resonator chamber tuned to the narrow frequency band of the airborne sound pressure field and having a dimensioned opening formed into a first endplate of the chambver for admitting the airborne sound pressure field. Mounted within the resonator chamber is a transducer circuit comprising a microphone and a pre-amplifier, the microphone functioning to detect the resonating sound pressure field within the chamber and to convert the resonating sound waves into an electrical signal while the pre-amplifier functions to amplify the electrical signal for transmission via a cable to an underwater or surface marine vehicle to undergo signal processing.

Abstract: The invention is a butterfly-type check valve (8) wherein the valve plate (18) moves translationally relative to a pivot axis (90) and incident to its own rotational movement. The invention employs biasing means (102, 104, 108) for initiating movement of the valve plate when the latter is at a closed rotational position, thereby eliminating the need for a pilot valve.

Abstract: Ceramic turbine wheels are balanced to minimize rotational vibrations by bonding silica-based glass pads to the wheel. The pads are formed from a mixture of sodium silicate, water and a fine ceramic powder, preferably of a composition similar to the underlying ceramic turbine wheel. The weighted pads are machined, without damage to the underlying ceramic wheel, to achieve proper balance.

Abstract: A butterfly-type check valve (8) in which a valve plate (18) moves translationally relative to a pivot axis (90) and incident to rotational movement (118) of the plate. The translational movement is effected by mechanical links (38, 40) which are pivotally secured to the plate and a support assembly (52, 54, 56, 76, 78). The translational movement is guided by two trunnions (30, 32) pivotally secured to the support assembly, and two rods (20, 22) rigidly secured to the plate and extending through the trunnions.

Abstract: An air turbine starter for use aboard aircraft includes a dual range power train and a clutch automatically shifting between the ranges according to the use being experienced by the starter. Main engine starts may be achieved more quickly, while ground check out of aircraft systems using the starter to power main engine accessory devices via the engine gear box may be performed with better power input to the accessories and improved efficiency.

Abstract: A radial inflow particle separator includes a pair of axially and radially spaced curvilinear walls cooperatively defining a circumferential flow path leading radially inwardly and axially to an engine. Preferably, the particle separator is employed with a turbine engine which is operated at times in an environment laden with dust and particulate matter. Such an environment is typically encountered by a turbine engine of a helicopter, or off-road vehicle. The particle separator provides dust and particulate control features including aero-inertial, particle trajectory, particle boundary-rebound, and scavenge flow tailoring to achieve a dust and particulate separation efficiency as good as or better than the best conventional axial-flow particle separators. This particle separation effectiveness is achieved in a radial inflow particle separator which is smaller and lighter in weight than axial flow devices, and which packages advantageously with the essential structures of a turbine engine.

Abstract: A method and apparatus for varying the effective area of a jet engine exhaust nozzle. The apparatus includes a center body disposed upstream of the nozzle throat and configured to form a recirculation wake extending to and through the nozzle throat. The conditions of fluid flow are selectively variable, for example, by axial movement of a portion of the center body, to vary that portion of the nozzle throat which is effectively blocked by the recirculation wake so as to be unavailable for downstream motive fluid flow.

Abstract: A fuel manifold (70) for a gas turbine engine is formed from a plurality of spaced bodies (10) and interconnecting conduits (72). The bodies (10) are adapted to provide fluid communication between the conduits (72) and a corresponding plurality of nozzle assemblies (62) which are removably secured to the bodies. The nozzle assemblies (62) can thereby be detached from a structure (58) to which the manifold (70) is secured, while all components (10, 72) of the manifold (70) remain secured to the structure (58) and to each other. A fail-safe sealing member (32) adapted for use with the fuel manifold/nozzle assembly combination (70, 62) is also disclosed.

Abstract: A high temperature turbine engine includes a rotor portion having axially stacked adjacent ceramic rotor parts. A ceramic/ceramic joint structure transmits torque between the rotor parts while maintaining coaxial alignment and axially spaced mutually parallel relation thereof despite thermal and centrifugal cycling.

Abstract: a balanced butterfly valve method and apparatus having a valve plate pivotally supported within a mounting body. The valve plate is capable of both rotational and translational movement in response to rotation of an input shaft. A spring is provided to resist translational movement of the valve plate. Differential gearing is used to convert rotational movement of the input shaft into rotational and translational movement of the valve plate depending on the relationship between the force exerted by the spring and the torque exerted on the valve plate by the fluid.

Abstract: A binary counter (60) provides for resolution doubling by producing a wavetrain (Q0) which represents the zero-order bit of the counter and has the same frequency as the clock input (REFCLOCK).

Abstract: A combination air data probe performs a number of different pressure measurements from a single structure. Measurements of total pressure and total temperature are performed in an improved structural configuration which renders these measurements substantially insensitive to aircraft angle of attack. Static temperature is computed free of recovery factor error because of compensatory effects in the pressure and temperature signals. Another part of the probe provides measurement of static pressure and pressures for determining angle of attack.

Abstract: A gas turbine engine is provided with hollow guide vanes having thermally responsive actuators mounted within each for individually controlling the cooling air flow therethrough in response to local temperature variations.