Abstract: A thermal regenerative injector 10 for a rocket engine that transfers heat from a fuel after turbine operation to the fuel prior to turbine operation, thereby providing a higher chamber pressure and lower fuel pump pressure. The injector 10 has a plurality of elements 44 having concentric channels 78, 80, and 82 separated by sleeves 66, 68, and 70, the fuels flowing therethrough, heat being transferred through a common middle sleeve 68, The cold fuel, after being so heated, is heated further in the typical fashion of routing it through the combustion zone and nozzle cooling jackets 16 and 20.

Abstract: Means for sealing the tip 18 of a rotor turbine blade 10 against tip leakage flow comprising a multiplicity of recesses 30 formed in the surface of the tip 18. The recesses 30 are preferably formed in a labyrinthine or slaggered pattern which interposes at least one recess 30 in every leakage flow path across the tip 18 from the pressure side 26 to the suction side 28 of the blade 10.

Abstract: A downhole steam-generating system in which fuel and compressed air from an air compressor unit 20 are fed to a steam generator 22. Steam and/or combustion products are fed to the turbine 24 from the steam generator 22 and the turbine 24 is used to mechanically drive the air compressor unit 20. After leaving the turbine 24, the turbine output may be scrubbed and the combustion products may be either passed down the borehole with the steam or may be discharged into the atmosphere.

Abstract: A closed Rankine-cycle power unit 10 for powering a turbine 16. The unit comprises a single closed loop in which a working fluid is circulated. The fluid, in liquid phase, is brought to gaseous phase by passing it through a heat exchanger 14 and the gas is used to drive a turbine 16. The gas is then passed through supersonic condenser 20 of supersonic condenser-radiator 18. Supersonic condenser 20 comprises a supersonic DeLaval nozzle 30 connected to a long barrel 38 which converts the gas stream into liquid droplets. The droplets are formed into a droplet beam 22 by a spray nozzle 40, the droplets radiating away a large amount of their heat energy. The beam 22 is collected as a liquid by a collector 24 and pumped through a compressor 26 which raises its pressure. The liquid from the compressor 26 is then circulated through the heat exchanger 14 again.

Abstract: The present invention provides a rocket thrust chamber (30) comprising a combustor (32) with a fixed divergent profile, a nozzle (36) for further expanding the output of the divergent combustor and a high-velocity, throttleable injector (34) for injecting propellants at such an initial velocity and initially rapid, axial burning rate that the injected propellants achieve sonic flow conditions at preselected locations within the divergent combustor according to throttle setting. In operation, the throttle setting fixes the location of the sonic flow line within the divergent combustor, and the ratio of the nozzle exit area with respect to the effective area of the divergent combustor at the sonic location area fixes the expansion ratio for that throttle setting. At launch, the engine delivers a high propellant flow rate and a moderate expansion ratio, while in space, it delivers a low propellant flow rate and a far greater expansion ratio.

Abstract: An improved structural material for the wall of a rocket engine nozzle extension comprising a thin sheet-metal base 12 and a rib wall 16 comprising a grid of intersecting ribs 18 which form internal cavities 20. A surface of the base 12 is plated 14 with Cu and the rib wall 16 is bonded thereto so that each cavity 20 has an open end. The interior surfaces of the ribs 18, which form the cavities 20, are also plated with Cu.

Abstract: An improvement in the design of a staged-combustion-cycle rocket engine. The preburner 16 (or preburners) is operated at a higher temperature than that above which turbine blades will be damaged. A heat-exchanger unit 40 through which the output flow of the cooling jacket 18 of the engine is passed is placed inside the preburners 16, or in close proximity to its output flow, so that heat energy is transferred from the output flow of the preburners 16 to the output flow of the cooling jacket 18. This lowers the preburners output flow to a temperature which will not damage turbine blades and raises the cooling-jacket output flow temperature. Since the output flow of the cooling jacket 18 is fed to the low-pressure turbines 22, the increased temperature raises the pressure of the low-pressure turbines 22 so that their output of flow rate is increased and the flow rate to the engine is increased, thereby increasing engine output power and efficiency.

Abstract: A heat-regenerative, expander-cycle, turbine-drive rocket engine 26 in which heated oxidizer gas is used to drive the fuel and oxidizer turbines 16 and 20. The hot exhaust gas from the oxidizer turbine 20 is passed through a heat-donor coil 36 of a heat exchanger 24 where it passes heat to the oxidizer flowing through a donee coil 34 to preheat the oxidizer liquid and gasify it before it is passed through the cooling jacket 28 of the rocket engine 26 where it cools the engine 26 and is itself heated to a higher temperature. The oxidizer, e.g., N.sub.2 O.sub.4, is brought to higher temperature and pressure than its supercritical temperature and pressure so that flashing and boiling of the oxidizer are avoided.

Abstract: An internally manifolded plate for a plate/fin-type heat exchanger comprises a side port contiguous with and transverse to at least one channel, and wherein the channel is contiguous with an end port. The plate may be of unibody construction and also include integral side and end external manifolds.

Abstract: An internally manifolded plate for a plate/fin-type heat exchanger comprises a side port contiguous with and transverse to at least one channel, and wherein the channel is contiguous with an end port. The plate may be of unibody construction and also include integral side and end external manifolds.

Abstract: An internally manifolded plate for a plate/fin-type heat exchanger comprises a side port contiguous with and transverse to at least one channel, and wherein the channel is contiguous with an end port. The plate may be of unibody construction and also include integral side and end external manifolds.

Abstract: The present invention provides a steam generator which comprises rocket-type multielement injector head and a small diameter, highly elongated, cylindrical combustion chamber whose walls are formed from a plurality of longitudinally adjoined water tubes. The multielement injector head injects an array of associating streams of fuel and oxidizer into the combustion chamber under sufficient pressure to maintain a combustion pressure in the range of 25-150 psia whereupon the narrowness of the combustion chamber serves to constrict the resultant combustion gases to thereby promote radiant and convective heat transfer from the flame of combustion through the walls of the combustion chamber into the water passing through the water tubes. By such arrangement the production of nitrogen oxides in the combustion chamber is avoided.

Abstract: In combination with a diesel engine, a preheater 10 for diesel fuel generally comprises a hot fluid chamber 12 having a first open end 14, a second open end 16, and perimeter walls 17. As the engine cooling water exits from the engine block, it passes through hot fluid inlet 18 into hot fluid inlet manifold 20, through chamber 12, and out through fluid outlet manifold 22 and hot fluid outlet port 24. Located along the top and bottom perimeter walls 17 of chamber 12 are heat exchanger plates 26 for carrying diesel fuel. Interconnected with plates 26 are fuel inlets 28, fuel inlet manifolds 30, fuel outlet manifolds 32, and fuel outlets 34.

Abstract: An internally manifolded plate for a plate/fin-type heat exchanger comprises a side port contiguous with and transverse to at least one channel, and wherein the channel is contiguous with an end port. The plate may be of unibody construction and also include integral side and end external manifolds.

Abstract: Direct firing downbole steam generator basically comprises an injector assembly axially connected with a combustion chamber. Downstream of the combustion chamber and oriented so as to receive its output is a heat exchanger wherein preheated water is injected into the heat exchanger through a plurality of one-way valves, vaporized and injected through a nozzle, packer and check valve into the well formation.

Abstract: A tube-in-tube shelless heat exchanger having the capability of being modularized comprises a plurality of single element tube rows 18 in combination with header means 26. The single element tube row 18 comprises a plurality of inner 12 and outer 14 concentric tube pairs for carrying a first and a second heat transfer fluid, forward and aft tube sheets 20, and flexible arcuate manifold means 16 for outer tubes 14.

Abstract: A slide guide 22 for a tube-type heat exchanger has a tubular geometry and comprises saddle 28 and slots 26 interposed one each between fingers 24. Saddle 28 positions slide guide 22 within tube support sheet port 30 while fingers 24 are biased so as to conform to the ovality of tube 12 and dissipate dynamic loads across a relatively large tube surface area.

Abstract: A precombustor 10 for use in diesel engines comprises a precombustion chamber 12, a fuel spray nozzle port 18 through which a fuel spray nozzle 20 may be incorporated into the precombustion chamber 12, an igniter port 22 for an ignition means adjacent to said spray nozzle port 18, and a supersonic DeLaval nozzle 14 integrally incorporated into the precombustion chamber 12 opposite said spray nozzle port 18 for enhancing the injection of air into the precombustion chamber 12. Axially connected to the throat area of the DeLaval nozzle 14 is a two-dimensional subsonic diffuser 34 and flow passage 30 for transferring air from the diesel piston to the precombustion chamber 12 and combustion gases from the precombustion chamber 12 into the diesel cylinder.

Abstract: A geometrically optimized precombustion chamber 12 for a diesel or stratified charge engine is provided which limits the maximum gas temperature through transonic and/or supersonic flow to prevent the production of nitrous oxides and is defined in accordance with the following equation: ##EQU1##