Abstract: A turboprop engine having a variable pitch propeller driven through a speed reducing transmission. The engine has a compressor section with a low pressure component and a high pressure component. A flow control device is positioned between the low and high pressure components. During takeoff, air from the low pressure component is bypassed, and during cruise, the air from the low pressure component is passed directly through the high pressure component, thus obtaining improved matching of engine components for both takeoff and cruise.

Abstract: A gas turbine engine infra-red radiation suppressor comprising an exhaust nozzle which is surrounded by a duct having a plurality of diffuser vanes at its downstream end. The exhaust nozzle and duct constitute an ejector which is powered by the exhaust efflux from the exhaust nozzle and draws ambient air into the duct through a gap between the exhaust nozzle and the duct. The air serves to cool the exhaust efflux and thereby reduce its infra-red radiation emission, and the diffuser vanes prevent direct line of sight of the hot exhaust nozzle.

Abstract: A fan jet engine construction in which the drive connection between the rotor drive shaft (10) and the gearbox (18) includes a slideable tower shaft member (26) movable to a first position permitting removal of a drive module (16) and to a second position permitting removal of the fan casing (20) without removal of the gearbox.

Abstract: An oil delivery system for supplying oil to seal a portion of a turbomachine is disclosed. Specific means for routing oil at a desired temperature to an overhead tank are disclosed such that should oil from the overhead tank be required, as in an emergency or shutdown condition, then the oil being supplied from the tank will be at or near the temperature of the oil being supplied during normal operating conditions.

Abstract: A variable area air system means for air blast type fuel nozzles for use in gas turbine engines wherein fuel/air ratios are controlled for the purpose of controlling engine emission products to meet mandated emission standards over a wide range of engine operating conditions. The variable area air metering means is connected with a pressure responsive actuating means for controlling the air flow in single fuel system and dual fuel system air blast type fuel nozzle and support assemblies used in gas turbine engines.

Abstract: A cooling system 46 for a turbofan gas turbine engine 10 is disclosed. Various construction details which increase the effectiveness of a heat exchanger 70, 76, 112 are disclosed. In one embodiment, a rotor shaft 98 is used to pressurize buffer air for a bearing compartment 40.

Abstract: Exhaust gas is recirculated from the exhaust stack of a gas fired turbine to the air inlet along a constantly-open path to prevent inlet freeze-up. When anti-icing is not needed the exhaust stack is fully opened, creating a partial vacuum in the exhaust stack. At the turbine inlet the recirculation line, is opened to atmosphere. The resultant pressure differential between the opposite ends of the recirculation line creates a driving force for positively purging the recirculation line of unwanted residual exhaust gases. This in turn eliminates a source of unwanted moisture which could otherwise condense, freeze and interfere with turbine operations.

Abstract: A ducted fan type model aircraft power plant having a mounting for a one cylinder internal combustion model aircraft engine. The preferred engine utilizes a special vertically oriented carburetor. A duct is supported by a set of stators having an aerodynamic shape for straightening airflow through the duct. A fan having seven identical individual replaceable blades is disposed at the front of the duct and directly driven by the engine. One stator is adapted to essentially enclose the vertical carburetor and to smoothly direct the airflow from the fan around the carburetor to the engine cylinder for cooling. The stator has an opening to the carburetor air inlet for providing air under pressure thereto. The stator shapes cooperate with the duct and aft fairings of the power plant to deliver a smooth airstream having a uniform non-turbulent flow to produce a maximum propulsive efficiency.

Abstract: A stator structure 88 for supporting a pair of outer air seals 62, 72 and an array of stator vanes 82 from two axial locations A.sub.1, A.sub.2 on a coolable outer case is disclosed. Various construction details which enable the structure to respond to the movement of coolable rails are disclosed. In one embodiment, a pair of support rings 96, 100 and a pair of support rings 122, 124 extend between the outer case and the outer air seal and array of stator vanes 82.

Abstract: A device is provided for passing a fluid flow across a static or rotating barrier wherein there is relative rotation between the flow and the barrier and wherein it is necessary to pass the maximum of flow through the device while keeping the diameter of the device as small as possible.One embodiment of the invention shown in FIG. 2 is a device for use in a gas turbine engine for supplying cooling air across a bolted joint to a space behind a cover plate 6 for cooling an engine disc. The device comprises a cylindrical receiver 11 having helical slots 13 running through it from one axial end face to the other, the helix angle being the same as the angle of the relative velocity vector between the flow and the slots.The helical shape of the slots ensures that the radius of the axis of each slot is constant along the length of the slots and allows greater slot height and hence greater flow area.

Abstract: An anti-icing system for a rotating blunt nose bullet of a gas turbine engine uses a rotating thermosyphon effect to create a circulation within a chamber connected for rotation with the nose bullet which draws hot air from a downstream region of the engine forwards to impinge on the nose bullet over a small region close to the engine axis. This avoids complications with separate hot air supplies or electrical heaters. As shown in FIGS. 3 and 4 of the drawings, in one embodiment of the invention the chamber consists simply of a tube closed off by the nose bullet and in combination with an engine main shaft which extends to the turbine region of the engine to draw hot gas from this region. Alternatively, the chamber may extend only to the downstream end of the first compressor.

Abstract: The control device comprises at least one control ring to which one end of n elbow lever is articulated. The vane pivot of alternating vanes is fixed at the intersection of the arms of the elbow levers. The other end of each elbow lever is connected by a rod to the end of a straight lever, the other end of which is fixed to the pivot of an adjacent vane. The circumferential movement of the ring causes the pivots of the adjacent vanes to pivot in opposite directions. Two other embodiments have two rings.

Abstract: An air/oil heat exchanger is relatively interconnected to the compressor discharge air or fan discharge air of a fan-jet engine to minimize the size of the heat exchanger core so as to be able to locate the heat exchanger within the intermediate case between struts. The plumbing may be combined with the surge bleed system to simplify the systems and reduce weight and cost.

Abstract: A thrust reversing system for controlling the fan gases from a thrust producing aircraft engine. The system comprises a first group of blocker doors surrounding the upper longitudinal portion of the engine fan duct; a second group of blocker doors positioned rearward of the first group surrounding the entire engine fan duct; mechanism is provided for translating an upper movable fairing and a lower sleeve section which during translating provides an upwardly directed opening from the fan duct through gas-directing cascades and deploys the blocker doors from a stowed duct wall lining position to a deployed fan gas blocking deployed position.

Abstract: A self-actuating nozzle guide vane assembly for a turbine type power plant fuel nozzle increases airflow during the higher power regimes. The fuel nozzle inlet guides employ primary and secondary swirlers where the primary swirlers continuously deliver compressor air around the fuel nozzles and the secondary swirlers deliver compressor air solely when the pressure drop across the front end of the burner reaches a predetermined level in one embodiment or the inlet temperature goes above a predetermined threshold value in another embodiment.

Abstract: A shaft sealing apparatus utilizing a flow of sealing fluid to block leakage of a second fluid; and including a valve element controlling the flow of sealing fluid as a function of shaft rotational speed.

Abstract: An essentially all ceramic turbocharger for boosting the pressure of air inducted by an internal combustion engine has a housing made in two segments from ceramic material that define exhaust gas inlet and outlet passages and air inlet and outlet passages. A rotary unit formed of ceramic material is formed integrally with a turbine rotor and compressor rotor at opposite ends of the driveshaft. The driveshaft is supported within the housing on ceramic ball bearings whose races are surfaces formed on the driveshaft and housing segments within which ceramic radial and thrust bearings are fitted.

Abstract: An exhaust-gas turbocharger has a bearing system which is positioned between a compressor impeller and a turbine wheel which are positioned on respective ends of a rotor shaft. The compressor impeller is attached to the rotor-shaft via an intermediate bush. A conically mating fit, at one end of the intermediate bush directly adjacent to the bearing, serves to attach this intermediate bush to a shaft-stub of the rotor shaft. A frictionally-locked press fit serves, at the other end of the intermediate bush, to attach the compressor impeller to the intermediate bush, in a manner which transmits torque.

Abstract: A liquid expulsion apparatus 12 having a rolling diaphragm 20 conforming to the non-circular shape of the storage tank shelf 30, thereby increasing liquid storage capacity within the tank. A gas-driven piston 24, also conforming to the non-circular shape, expels the liquid in rapid fashion and provides the force for rolling the attached non-circular diaphragm 20. Stability in diaphragm 20 during actuation of piston 24 is maintained by varying the local thicknesses t of diaphragm 20 in relationship with the local, cross-sectional radii of curvature R.sub.c.

Abstract: Jet propulsion powerplant comprising a gas producer 11 having a first flow duct 12 for receiving the output of the gas producer 11. The flow duct 12 includes a nozzle 13 having a center body 16 which has an upstream part 17 and a downstream part 20. Motors 22 are provided for expanding and contracting the downstream part 20 relative to the upstream part 17. A second flow duct 33 having an inlet 30 openable to airflow and connected to the interior of said upstream part 17 is provided. An outlet 24 from the interior of the upstream part 17, is provided at the downstream end of the upstream part 17. The outlet 24 opens into the interior of the first flow duct 12 by contracting the downstream part 20 relative to the upstream part 17. By such an arrangement, infrared radiation may be suppressed when necessary by opening the inlet for air flow and controlling the upstream and downstream parts so that there can be a mixing of air with exhaust gases which reduces the mean temperature of the exhaust gases.