Abstract: A fan-turbine rotor assembly (24) for a tip turbine engine (10 )includes a fan hub (64) with an outer periphery (112) scalloped by a multitude of elongated openings (114) which extend into a fan hub web (115). Each elongated opening defines an inducer receipt section (117) to receive an inducer section (66)and a hollow fan blade section (72). An inducer exhaust from each inducer section is located adjacent a core airflow passage (80) within each fan blade section to provide communication therebetween.

Abstract: A tip turbine engine has a more efficient core airflow path from the hollow fan blades, through the combustor and to the combustion chamber of a combustor. The turbine engine includes a rotatable fan having a plurality of radially-extending fan blades each defining compressor chambers extending radially therein. A turbine is mounted to the outer periphery of the fan. A diffuser at a radially outer end of each compressor chamber turns core airflow through the compressor chamber toward the combustor. The high velocity, high pressure core airflow from the compressor chambers in the hollow fan blades is diffused before the compressed core airflow enters the combustor, thereby improving the efficiency of the tip turbine engine. Further, the overall diameter of the tip turbine engine is reduced by the arrangement of the diffuser case in a position not directly radially outward of the fan blades.

Abstract: A tip turbine engine (40) provides a peripheral combustor (30) with a more efficient combustion path through the combustor and through the tip turbine blades (34). In the combustor, the core airflow is received generally axially from compressor chambers in hollow fan blades (28) and then turned radially outwardly into a combustion chamber (112), where it is then mixed with the fuel and ignited. The combustor has a combustion path extending axially from a forward end of its combustion chamber through a combustion chamber outlet (122) and through a turbine (32) mounted to the fan. Thus, when the core airflow begins to expand in a high-energy gas stream, it has a substantially axial path from the combustion chamber through the turbine.

Abstract: A variable rotor blade mechanism for use in a gas turbine engine comprises a blade rotor, a blade, a harmonic drive system, a stepper motor and a bracket. The blade rotor rotates absolutely about an axial engine centerline during operation of the gas turbine engine. The blade extends radially from the blade rotor and is configured to be adjustable by rotation about a radial axis. The harmonic drive system is mounted to the blade rotor and connected to the blade to rotate the blade about the radial axis. The stepper motor drives the harmonic drive with relative rotational input with respect to the absolute rotation of the blade rotor. The bracket is disposed about the engine centerline and supports the stepper motor stationary with respect to the rotation of blade rotor such that the relative rotational input to the stepper motor is generated.

Abstract: A fan-turbine rotor assembly for a tip turbine engine includes an outer periphery scalloped by a multitude of elongated openings which define an inducer receipt section to receive an inducer section and a hollow fan blade section. Each fan blade section includes a turbine section which extends from a diffuser section.

Abstract: A seal assembly (118) mounted within a nonrotatable static inner support structure (16) for engagement with an axial seal face surface (114) and a radial seal face surface (116). The radial seal (120) engages the axial seal face surface and the axial seal (122) engages the radial seal face surface. The seal assembly provides minimal leakage of core airflow to increase the tip turbine engine operating efficiency.

Abstract: A seal assembly (116) mounted within a rotationally fixed static outer support structure (14) for engagement with an annular seal face surface (172) located upon a fan-turbine rotor assembly. The seal assembly provides minimal leakage of core airflow when the airflow is turned and diffused by the diffuser section (74) to increase the engine operating efficiency.

Abstract: A tip-turbine engine comprises a fan-turbine rotor assembly that includes one or more turbine ring rotors. Each turbine ring is assembled from a multitude of turbine blade clusters. By forming the turbine blades in clusters, leakage between adjacent blade platforms is minimized which increases engine efficiency. Assembly of the turbine blade clusters to a diffuser surface includes axial installation and radial locking of each turbine blade cluster. This is accomplished by attachment lugs protruding from the underside of the arcuate base of the turbine blade clusters. Torque load surfaces are also integrated into the arcuate base.

Abstract: A tip turbine engine comprises a fan-turbine rotor assembly that includes one or more turbine ring rotors. Each turbine ring is assembled from a multitude of turbine blade clusters. Assembly of a multitude of turbine blade clusters to a diffuser includes axial installation and radial rotation. The clusters are axially installed, then rotated toward a radial stop in a direction which will maintain each cluster against the radial stop during operation of the fan-turbine rotor assembly. A multitude of turbine rotor ring stages may also be locked together to future increase the rigidity of the turbine.

Abstract: A cooling system for a gas turbine engine includes a non-rotating component extending into an engine flowpath, a vapor cooling assembly configured to transport thermal energy from a vaporization section to a condenser section through cyclical evaporation and condensation of a working medium sealed within the vapor cooling assembly, wherein the vaporization section is located at least partially within the non-rotating component, and wherein the condenser section is located outside the non-rotating component and away from the engine flowpath.

Abstract: A heat exchange system for use in lubricating systems for aircraft turbofan engine equipment in which a lubricant is provided under pressure to spaces bounded at least in part by surfaces moving relative to one another, the heat exchange system for providing air and lubricant heat exchanges to cool the lubricant at selectively variable rates in the engine fan airstreams. A heat exchanger core is provided in a controlled air flow duct system opening at its plural entrances to the engine fan airstreams and having its outlet end opening about at the end of the fan duct nozzle.

Abstract: A fan-turbine rotor assembly (24) includes a multitude of turbine blades (34) which each define a turbine blade passage which bleed air from a diffuser section (74) to provide for regenerative cooling. Regenerative cooling airflow is communicated from the radial core airflow passage (80) through the diffuser passages (144), through diffuser aspiration passages (146A, 146B) and into the turbine blade passages (150a). The regenerative cooling airflow exits from the turbine blade passage (150a) and transfers received thermal energy into an annular combustor (30). The received thermal energy is recovered at the highest temperature in the cycle.

Abstract: A tip turbine engine has a more efficient core airflow path from the hollow fan blades, through the combustor and to the combustion chamber of a combustor. The turbine engine includes a rotatable fan having a plurality of radially-extending fan blades each defining compressor chambers extending radially therein. A turbine is mounted to the outer periphery of the fan. A diffuser at a radially outer end of each compressor chamber turns core airflow through the compressor chamber toward the combustor. The high velocity, high pressure core airflow from the compressor chambers in the hollow fan blades is diffused before the compressed core airflow enters the combustor, thereby improving the efficiency of the tip turbine engine. Further, the overall diameter of the tip turbine engine is reduced by the arrangement of the diffuser case in a position not directly radially outward of the fan blades.

Abstract: A tip turbine engine according to the present invention includes a plurality of independently variable inlet guide vanes for the fan and/or for the compressor. An actuator is operatively coupled to each of the flaps, such that each actuator can selectively vary the flap of its associated inlet guide vane. In one embodiment, the inlet guide vanes each include a pivotably mounted flap that is variable independently of the flaps of at least some of the other inlet guide vanes. In another embodiment, the inlet guide vanes each include at least one fluid outlet or nozzle directing pressurized air, as controlled by the associated actuator, to control inlet distortion.

Abstract: A fan-turbine rotor assembly for a tip turbine engine includes a fan hub with an outer periphery scalloped by a multitude of elongated openings which extend into a fan hub web. Each elongated opening defines an inducer section and a blade receipt section to retain a hollow fan blade section. The blade receipt section retains each of the hollow fan blade sections adjacent each inducer section. The inducer sections are cast directly into the fan hub which minimizes leakage between each fan blade section and each of the respective inducer sections to minimize airflow leakage and increase engine efficiency.

Abstract: A fan-turbine rotor assembly (24) includes one or more turbine ring rotors (32). Each turbine ring rotor is cast as a single integral annular ring. By forming the turbine as one or more rings, leakage between adjacent blade platforms is minimized which increases engine efficiency. Assembly of the turbine ring rotors to the diffuser ring (114) includes axial installation and radial locking of each turbine ring rotor.

Abstract: A combustor/coil assembly for direct electromagnetic induction from a detonation wave comprises an annular combustor, a magnetic field source and a port. The annular combustor comprises an inner liner and a coaxial outer liner. The outer liner is electrically insulated from the inner liner. The magnetic field source generates a substantially axial magnetic field inside the annular combustor. The port introduces reactants into the annular combustor to form the detonation wave. The detonation wave induces a voltage between the inner liner and the outer liner by forming a current loop between the inner liner and the outer liner.

Abstract: A tip turbine engine (10) provides an axial compressor (22) having a compressor case (50) from which extend radially inwardly a plurality of outer compressor airfoils (54). The compressor case (50) is directly driven by the rotation of the turbine (32) and fan (28), while at least one gear (77) couples the rotation of the turbine (32) and fan (28) to an axial compressor rotor (46) having a plurality of inner compressor airfoils (52). In this manner, the axial compressor rotor (46) is driven in a direction opposite the direction of the outer compressor airfoils (54), thereby increasing the compression provided by the compressor without increasing the number of airfoils. The outer compressor airfoils (54) are formed on a plurality of outer airfoil assemblies (56) each having an arcuate substrate (58) from which the outer compressor airfoils (54) extend. Each of the outer compressor airfoil assemblies (56) includes more than one axially-spaced stage of outer compressor airfoils (54).

Abstract: A tip turbine engine (30) includes a low pressure compressor (22) having a plurality of inlet guide vanes (55) that are mounted at an inlet to the compressor case (50). Each inlet guide vane (55) includes at least one fluid outlet (56) proximate a trailing edge of the inlet guide vane (55), such that fluid flow through the fluid outlet (56) modulates and controls the air flow into the compressor (22). A supply of pressurized fluid may be supplied from compressed air from the compressor (22).

Abstract: A seal assembly (118) mounted within a nonrotatable static inner support structure (16) for engagement with an axial seal face surface (114) and a radial seal face surface (116). The radial seal (120) engages the axial seal face surface and the axial seal (122) engages the radial seal face surface. The seal assembly provides minimal leakage of core airflow to increase the tip turbine engine operating efficiency.