Abstract: A linerless rocket motor is provided by the bonding of a reticulated support structure, which is embedded in an homogenous mass of propellant material including an oxidant, to the inner wall of the rocket motor case. An inexpensive, safe, and easy to manufacture igniter is comprised of an homogeneous mass of propellant material including an oxidant and a reticulated support structure embedded therein. A light weight, high crush strength, and high strain capability sliver for a rocket motor comprises a block of inert material and a reticulated support structure of carbon, graphite, or a non-combustible material embedded therein. A rocket motor is prevented from accidental propulsion during a fire by attaching a propellant block to the outer side of the rocket motor base. The propellant block burns and produces heat during the fire to weaken the motor case so that pressure resulting from burning of propellant in the rocket motor will burst a hole in the rocket motor case to relive the pressure.

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: The uprating of existing jet engines increases the operating temperatures within the engines and also increases the tendency for flashback in some afterburner type engines. Afterburner type engines include a pilot fuel delivery pipe which is included between inner and outer annular members of a flameholder. Downstream from the pilot, partitions direct an ignited fuel/air mixture into the afterburner chamber. The afterburner flame is downstream from the flameholder, but under conditions of increased temperature the afterburner flame will tend to migrate upstream toward the flameholder. To avoid this tendency, the flameholder includes means for discharging gas which cools the flameholder metal itself while also decreasing the downstream air temperature, thereby decreasing the potential for flashback. In one embodiment, fuel and oxygen depleted turbine discharge gas are used to further decrease the tendency toward flashback.

Abstract: An oil supply device has a reservoir adapted to contain oil having a predetermined oil level; a drive shaft extending into the reservoir; a disc affixed to the shaft and being arranged to be submerged at least partially in the oil contained in the reservoir; and a trough affixed to the disc for rotation therewith as a unit. The trough extends arcuately and is radially inwardly open as viewed relative to the disc. Further, the trough is arranged to be submerged at least partially in the oil contained in the reservoir. There is also provided an oil conduit having a stationarily supported terminal portion accommodated in the reservoir and projecting into the trough. The oil conduit is provided with an open end situated in the trough and oriented opposite an operational rotary direction of the disc, whereby oil is driven into the terminal portion through the open end from the trough upon rotation of the drive shaft to supply oil under pressure in the oil conduit.

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: Floating panel heat shields 26 cover the walls of a combustor with a portion of the cooling air 32 passing upstream. The dome heat shield 36 has a lip 42 overlapping a portion of the wall hot shield 26. Dome 16 at location 44 deflects cooling flow 32 forcing it inwardly against lip 42 to improve cooling of lip 42.

Abstract: A solid fuel turbine engine comprises a centrally disposed axially extending shaft having an annular combustion chamber disposed thereabout intermediate the ends thereof. A compressor is mounted at one end of the shaft for delivering air to the combustion chamber to provide the principal source of oxygen for combustion and a turbine is mounted at the other end of the shaft. The turbine is driven by combustion gases and drives the compressor. An annular solid fuel charge is disposed in the combustion chamber for producing combustion gases.

Abstract: A surface, of an inner sleeve of a combustion apparatus for a gas turbine, which is subjected to a flame radiation heat is coated with a ceramic coating. A coating which is superior in high temperature corrosion resistant characteristics to a metal material forming the inner sleeve is provided on the opposite surface of the inner sleeve. Thus, heat transferred to the inner sleeve by the radiation from the flame is shielded by the ceramic coating. A formation of oxides on the coating of the corrosion resistant metal material formed on the opposite surface of the sleeve is prevented. A heat release through the surface from the metal material forming the inner sleeve is enhanced, whereby a thermal stress generated in the inner sleeve is suppressed to thereby prevent a generation of a cracks.

Abstract: A combined fuel distribution and flameholding system (14) includes an improved spraybar (16) having a tapered portion (28) and a radially inwardly disposed tip portion (30). The tapered portion (28) is configured to provide a flow profile (26) diminishing with respect to inward radial displacement from the burner wall (32) for achieving a uniform blockage to free flow area ratio within the burner. The tip portion (30) creates a turbulent or pilot region (32) in the center of the burner, providing a local environment well suited for ignition and low load burner operation. The individual bars (16) are releasable (46) from the exterior of the burner for allowing longitudinal withdrawal of the entire spraybar (16) through a corresponding opening (48) in the burner wall (22).

Abstract: A crossfire tube assembly joining adjacent combustors in a gas turbine engine includes an impingement sleeve within which a crossfire tube is centrally disposed. The impingement sleeve is pierced by an array of impingement cooling holes which form a plurality of small jets of cooling air impinging upon, and cooling, the crossfire tube. The space between the impingement sleeve and the crossfire tube forms a flow channel along which the spent impingement air flows in the axial direction before exiting into the interiors of the combustors. A flow dam at the center of the flow channel forces the impingement air to flow toward the ends. An outward flare in a portions of the crossfire tube extending beyond the extremity of the impingement sleeve directs air exiting the flow channel upon an annular flange which supports the crossflow assembly and thus improves cooling in this area.

Abstract: A radial flameholder (18) extends from the augmentor case (22) through an opening (30) in a coaxial liner (20) and into the hot exhaust gas stream (26). A portion of a cool, annular fan air stream (28) enters an upstream facing opening (34) and discharged radially inwardly adjacent the downstream edge (44) of the liner opening (30). The inner flow (42) of cool air protects the liner (20) downstream of the flameholder (18) by both cooling the liner (20) locally and by displacing the combustion reaction (32) attached to the flameholder (18).

Abstract: It has been found that in a dry low NOx combustor of the type having an upstream combustion chamber and a downstream combustion chamber interconnected by a venturi section, the fuel-air ratio and uniform fuel-air mixing can be improved by providing an annular shield upstream of the venturi region. The shield is impingement cooled through the venturi and provision is made for dumping cooling air farther downsteam in the downstream combustion chamber. With the aforesaid improvements in mind, the upstream combustion chamber is provided with first and second inner liners which are also impringement cooled an which provide combustion air farther upstream into the upstream combustion chamber to further improve fuel-air mixing and to maintain the desired fuel-air ratio.

Abstract: A dual mode, dual stage low NOx combustor, includes a primary combustion chamber and a secondary combustion chamber separated by a throat region of reduced diameter. Fuel is input into the primary combustors by an annular array of diffusion type nozzles whereas in accordance with the invention fuel is input into the secondary combustor by a central combination premix and diffusion nozzle.

Abstract: The present invention relates to a mechanical and insulating connection between, on the one hand, a filament-wound casing, constituting a wall for the combustion chamber of a solid propellant rocket motor, and on the other hand, a hot nozzle made from a heat-conducting refractory material wherein said connection consists of a single connecting ring fixed to the nozzle and resiliently connected to the wound casing, which ring is made from a low density insulating material, resistant to mechanical forces, as well as to mechanical shocks and thermal stresses, preferably a composite material with multidirectional reinforcements and a ceramic matrix.

Abstract: A solid rocket motor grain construction is disclosed for use in a ramjet to improve performance. The solid fuel burn enhancer adds oxidizer for burn rate control. Two constructions are disclosed. The inlaid approach places cores of solid low-oxidizer fuel within solid unoxidized fuel and the integrated approach provides shells of low oxidizer around the solid unoxidized fuel. The low-oxidizer fuel has a faster burn rate and smaller burn area requirements than the unoxidized fuel. During initial ramjet operation, when the burn area is constrained, the low-oxidizer fuel burns initially with its smaller burn area requirements. Subsequently, the conventional unoxidized fuel burns when larger burn areas are available.

Abstract: A heat recovery system for taking out a mechanical energy from hot exhaust gas from a gas turbine comprises at least two exhaust-gas boiler each having drum of an interior pressure different from each other, a steam turbine, a generator driven by the steam turbine, steam condenser and a plurality of heat exchanger. The heat exchanger is disposed in advance of the drum of the respective exhaust-gas boiler so that a feed-water circulating through the heat recovery system is pre-heated before entering into each drum by means of a cooling water which is used to cool blades of the gas turbine and becomes very hot.

Abstract: An apparatus and method are disclosed which ensures that a rotor-shaft assembly is in rotational balance after assembly of the individually balanced components by preventing the creation of any imbalance during assembly. The rotor member is formed with an annular groove about the nose portion at a point near its mounting face, which during assembly is crimped before any shaft bending occurs, thereby eliminating any rotor-shaft imbalance.

Abstract: A nozzle guide structure (10) is provided for receiving a fuel nozzle (34) in an opening (30) in a planar bulkhead (28) of a combustion chamber (12). The guide structure (10) includes an inner bushing (44), a transverse heat shield (46), and an annular retainer (52) disposed opposite the heat shield (46) with respect to the bulkhead (28). Flow openings (62) disposed in the retainer (52) admit cooling air (64) into an annular gap (50) formed between the bushing (44) and the bulkhead (28). the cooling air (64) subsequently flow between the bulkhead (28) and the heat shield (46) to provide cooling thereto.

Abstract: In a metal-ceramic combination wherein a monobloc ceramic member comprising a base, a protrusion integrally formed on the base and an easement portion on and around the root of the protrusion, is combined with a metallic member, an improved combination having an excellent strength in total is obtained by fitting the protrusion tightly into a recession or conduit of the metallic member, leaving clearance of 0.5 mm or more between the easement portion and a defined edge of joint interface of the said two members. The combination of the invention is particularly useful for engine parts to be subjected to high temperatures and repeated stresses such as a turbocharger rotor, piston, tappet, rocker arm, exhaust valve, cam and the like.

Abstract: In a combined cycle power plant operable on either gas or liquid fuels maximum design efficiency is achieved at the lowest HRSG stack temperatures. This can be optimized for operation on natural gas but for liquid fuel operation consideration must be given to sulfur cold end corrosion. A feedwater recirculation loop is shown which allows for selectively heating feedwater during liquid fuel operation and for non-heating during gas operation. Economizer recirculation is also introduced to prevent economizer steaming.