Abstract: A gas turbine for starting an aircraft engine and for driving auxiliary equipment, being normally run by combustion, receives decomposition gases of hydrazine, selectively on a standby basis, whereby aircraft engine fuel is added to these gases, and the mixture is then fed to the turbine to drive the turbine without combustion.

Abstract: Between the rotor and stator components of turbomachines, compressors, pressure wave machines and the like, the clearance space is partially filled out by an abradable element which is capable of "growing" when subjected to an elevated temperature and/or to the influence of the particular atmosphere in which the machine operates. As the element grows, it compensates for corrosion and erosion factors which take place in the machine and which otherwise tend to increase the clearance. Suitable materials which will "grow" under these operating conditions are gray cast iron and a sintered graphite-metal.

Abstract: A bearing lubrication system for a turbine engine is provided which utilizes a fuel-air mist to both lubricate and cool the bearing assembly. An annular fuel-air distributor is positioned adjacent the bearing assembly and includes an inlet and several outlet ports directed towards the bearing assembly. A fuel port and a source of pressurized air are coupled to the inlet of the fuel-air distributor so that the pressurized air mixes the fuel into the air and projects a fuel-air mist through the distributor and onto the bearing assembly. A fuel metering device maintains the fuel-air ratio outside of its flammability range to prevent fires within the bearing cavity. Exhaust passageways from the bearing cavity are disposed adjacent the bearing outer race to provide additional cooling of the bearing assembly during the exhaustion of the fuel-air mist from the bearing cavity.

Abstract: A stationary gas turbine plant in which a bearing for the bladed rotor is located at the exhaust end of the casing where the flow passage for the exhaust gas merges into an annular diffusor ring surrounding the bearing housing and which is established by radially spaced circular walls interconnected by means of an array of circumferentially spaced radially extending aero-foil shaped ribs. Two of these ribs extending divergently in a generally downward direction toward the foundation for the turbine are made hollow for the purpose of passing support struts through them, the upper ends of these struts being secured to the bearing housing and the lower ends of the struts being secured to the foundation. Additional supports are provided at opposite sides of the casing at the exhaust end, these supports also being secured to the foundation.

Abstract: Axial flow turbomachinery having an impeller with a plurality of contoured blades mounted within a diffuser throat and about a central rotatable hub. This blade shape is defined by the ratio of the blade root and tip chords to the minimum midsection blade chord, which is between about 1.25 and about 2.25. The ratio of blade pitch at the root and tip sections as compared with the blade midsection pitch is preferably between about 1.0 and about 1.4.This configuration of a preferred diffuser is described by the following relationship: ##EQU1## Where A.sub.t is the diffuser cross-sectional area at the diffuser throat, A.sub.o is the diffuser cross-sectional area at the outlet, l is the diffuser length from the diffuser throat to the diffuser outlet, x is a distance along the diffuser measured from the diffuser throat toward the diffuser outlet, A.sub.x is the diffuser cross-sectional area x distance from the diffuser throat and n is a value between about 2 and about 4.

Abstract: In a gas turbine engine of the type which includes an inlet particle separator, there is provided apparatus for measuring the temperature of the air entering the engine compressor.A remote temperature probe is disposed in a feed duct having an inlet in flow communication with the engine inlet upstream of the particle separator and an outlet disposed intermediate the particle separator and inlet to the engine compressor. Airflow through the feed duct is generated by the pressure drop across the particle separator without the use of compressor bleed or other air sources which result in performance degradation of the engine. Temperature measurement errors during engine anti-icing are reduced by selectively cross-bleeding a predetermined quantity of anti-icing air into the feed duct during activation of the engine's anti-icing system. The response rate of the probe is significantly improved by enclosing the probe in an impingement heat transfer blanket.

Abstract: A stagnation sensing control for determining when a gas turbine engine has stagnated during a start phase of operation includes means for sampling the engine speed at a first predetermined point in time and means to hold the sampled speed in memory and further including means operative following a period of time to compare engine speed at the later point in time with the speed in memory and means operative if the speed increase is less than an established amount greater than the sampled speed in memory to produce an engine shutdown signal to operate engine starter and shut down circuits for terminating engine operation.

Abstract: A rotor fixing device for turbines comprising rotor support means independent of the bearing and including an inner ring member split into at least two sections and formed on its inner peripheral surface with grooves complementary with packing teeth formed on an outer peripheral surface of the turbine rotor, and an outer ring member split into at least two sections and secured to a turbine casin for supporting the inner ring member, and means secured to stationary members of the turbine and adapted to be inserted into a space defined between a rotor wheel and a packing case head for constraining axial movement of the turbine rotor. The rotor support means is disposed adjacent each end portions of the turbine rotor. The turbine rotor can be fixedly supported in place in an assembled condition during transportation of the turbine. The rotor fixing device is removed from the turbine after completion of transportation thereof.

Abstract: The specification discloses a fireworks device including suspended body of flame dripping low molecular weight polyethylene material which produces a shower of flaming beads when ignited.

Abstract: A rocket motor nozzle closure for controlling the initial release of prese from the rocket motor nozzle to reduce the occurrence of high pressure shock fronts which are detrimental to the weapon operator. The mass and geometry of the nozzle closure are predetermined to fit the desired motor performance. The release of motor pressure is controlled by the rate of change of momentum of the nozzle closure.

Abstract: A hydraulic turbine having means for admitting air to the turbine draft tube. An annular air chamber about the draft tube has a plurality of circumferentially spaced openings into the interior of the draft tube. The pressure of the air in the air chamber is maintained below the maximum pressure of the water in the draft tube and above the minimum pressure of the water in the draft tube. This results in air entering the draft tube only at the areas of lowest water pressure and water entering the air chamber at areas of highest water pressure.

Abstract: A positioning device for varying a predetermined distance between a position sensor element and a rotor member disposed within a turbine apparatus. The positioning device comprises a concentric arrangement of rectilinearly displaceable members biased towards normal positions within a casing. Each member is displaced relative to the casing to either increase or decrease the predetermined distance between the sensor element and the rotor member.

Abstract: A rocket motor nozzle closure for controlling the initial release of prese from the rocket motor nozzle to reduce the occurrence of high pressure shock fronts which are detrimental to the weapon operator. The mass and geometry of the nozzle closure are predetermined to fit the desired motor performance. The release of motor pressure is controlled by the rate of change of momentum of the nozzle closure.

Abstract: A shroud closely surronding a high thermal inertia rotor is provided with a support structure having low thermal inertia characteristics. The support structure is selectively exposed to different temperature mediums during transient operation by way of a thermal actuated valve so as to cause a rapid growth thereof during periods of engine acceleration and a slow shrinkage thereof during periods of deceleration of the engine. In this manner the clearance relationship between the shroud and enclosed rotor is maintained at a minimum during periods of steady-state and transitional operation to thereby increase the efficiency of the combination.

Abstract: The gas turbine regeneration package is designed to increase the efficiency of gas turbines with exhaust gas recirculation. Besides the gas turbine itself, four basic components are used to make up the efficiency package: the first is an exhaust gas cooler, the second is an exhaust gas cooling fan, the third is a recycle exhaust gas regenerator and finally there is a compressed ambient air regenerator. Other turbines have ambient air regenerators but they are not used in conjunction with a recycled gas stream so they tend to have high concentrations of NO.sub.x in their exhaust gases. The basic advantage of this regenerator package includes the following:A. increased efficiency of the turbine at full and reduced power settings,B. cooler turbine exhaust is emitted to the atmosphere,C. better control over the combustion process particularly the production of oxides of nitrogen,D. reduced noise, andE. the use of ambient air as part of the engine heat sink.

Abstract: A device for reducing the effect of "water hammer" type shocks in an hydraulic system. The system has a discontinuity in it created by a vapor-core pump, and the discontinuity, which occurs at less than full pump flow, is used to empty a succession of compartments connected in series through respective orifices.When full pump flow is required a "water hammer" type shock is generated upon disappearance of the discontinuity and this is dissipated in a series of smaller shocks at each of the successive orifices as the series of compartments becomes filled. The maximum shock pressure to which the system is subjected is thus reduced.