| Patent application number | Description | Published |
|---|
| 20080206056 | Modular Tip Turbine Engine - A tip turbine engine assembly includes a compressor module ( | 08-28-2008 |
| 20080219833 | Inducer for a Fan Blade of a Tip Turbine Engine - A fan-turbine rotor assembly for a tip turbine engine includes an inducer with an inducer inlet section and an inducer passage section in communication with a core airflow passage within a fan blade. Each inducer inlet section is canted toward a rotational direction of the fan-turbine rotor assembly such that the inducer inlet section operates as an air scoop during rotation of the fan-turbine rotor assembly. Both axial and centrifugal compression of the airflow occurs within the inducer passage section to effectively pump the airflow through the inducer section and into the core airflow passage. | 09-11-2008 |
| 20090071121 | COUNTER-ROTATING GEARBOX FOR TIP TURBINE ENGINE - A tip turbine engine ( | 03-19-2009 |
| 20090071162 | PERIPHERAL COMBUSTOR FOR TIP TURBINE ENGINE - A tip turbine engine ( | 03-19-2009 |
| 20090074568 | VARIABLE FAN INLET GUIDE VANE ASSEMBLY, TURBINE ENGINE WITH SUCH AN ASSEMBLY AND CORRESPONDING CONTROLLING METHOD - A turbine engine includes a plurality of variable fan inlet guide vanes. Where the turbine engine is a tip turbine engine, the variable fan inlet guide vanes permit the ability to control engine stability even though the fan-turbine rotor assembly is directly coupled to the axial compressor at a fixed rate. The fan inlet guide vanes may be actuated from an inner diameter of the fan inlet guide vanes. | 03-19-2009 |
| 20090110544 | INFLATABLE BLEED VALVE FOR A TURBINE ENGINE - A compressor for a turbine engine includes an inflatable bleed valve that selectively bleeds core airflow from the compressor. The bleed valve has an inlet leading from the compressor and a passageway leading from the inlet. An inflatable valve selectively obstructs the passageway based upon a controlled supply of high pressure air to the inflatable valve. The supply of high pressure air may be compressed core airflow from an area downstream of the inlet to the bleed valve. | 04-30-2009 |
| 20090120058 | Tip Turbine Engine Integral Fan, Combustor, and Turbine Case - A tip turbine engine assembly includes an integral engine outer case located radially outward from a fan assembly. The integral outer case includes a rear portion and a forward portion with an arcuate portion that curves radially inwardly to form a compartment. An annular combustor is housed and mounted in the compartment. Fan inlet guide vanes are integrally formed with the arcuate portion to form the integral case portion. The rear portion, forward portion, and fan inlet guide vanes are integrally | 05-14-2009 |
| 20090120100 | Starter Generator System for a Tip Turbine Engine - A starter-generator system for a tip turbine engine includes a starter motor with a fixed starter generator stator and a starter generator rotor. The fixed starter generator stator is mounted to a static inner support housing. The starter generator rotor surrounds the fixed starter generator stator and is engagement with the axial compressor rotor. | 05-14-2009 |
| 20090142188 | SEAL ASSEMBLY FOR A FAN-TURBINE ROTOR OF A TIP TURBINE ENGINE - A seal assembly ( | 06-04-2009 |
| 20090145101 | PARTICLE SEPARATOR FOR TIP TURBINE ENGINE - A particle separator ( | 06-11-2009 |
| 20090145105 | REMOTE ENGINE FUEL CONTROL AND ELECTRONIC ENGINE CONTROL FOR TURBINE ENGINE - A controller is mounted remotely from a turbine engine and provided with an independent power source ( | 06-11-2009 |
| 20090148273 | COMPRESSOR INLET GUIDE VANE FOR TIP TURBINE ENGINE AND CORRESPONDING CONTROL METHOD - A tip turbine engine ( | 06-11-2009 |
| 20090148276 | SEAL ASSEMBLY FOR A FAN ROTOR OF A TIP TURBINE ENGINE - A seal assembly ( | 06-11-2009 |
| 20090148287 | FAN BLADE WITH INTEGRAL DIFFUSER SECTION AND TIP TURBINE BLADE SECTION FOR A TIP TURBINE ENGINE - 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. | 06-11-2009 |
| 20090148292 | AXIAL COMPRESSOR FOR TIP TURBINE ENGINE - A tip turbine engine ( | 06-11-2009 |
| 20090148297 | FAN-TURBINE ROTOR ASSEMBLY FOR A TIP TURBINE ENGINE - A fan-turbine rotor assembly ( | 06-11-2009 |
| 20090155057 | COMPRESSOR VARIABLE STAGE REMOTE ACTUATION FOR TURBINE ENGINE - A turbine engine locates an actuator ( | 06-18-2009 |
| 20090155079 | STACKED ANNULAR COMPONENTS FOR TURBINE ENGINES - Improved annular components and improved methods for assembling annular components into a turbine engine are described with respect to an axial compressor having a plurality of annular compressor rotor airfoil assemblies ( | 06-18-2009 |
| 20090162187 | COUNTER-ROTATING COMPRESSOR CASE AND ASSEMBLY METHOD FOR TIP TURBINE ENGINE - A tip turbine engine ( | 06-25-2009 |
| 20090169385 | FAN-TURBINE ROTOR ASSEMBLY WITH INTEGRAL INDUCER SECTION FOR A TIP TURBINE ENGINE - 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. | 07-02-2009 |
| 20090169386 | ANNULAR TURBINE RING ROTOR - A fan-turbine rotor assembly ( | 07-02-2009 |
| 20090232650 | TIP TURBINE ENGINE AND CORRESPONDING OPERATING METHOD - 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. | 09-17-2009 |
| 20110142601 | VARIABLE FAN INLET GUIDE VANE ASSEMBLY, TURBINE ENGINE WITH SUCH AN ASSEMBLY AND CORRESPONDING CONTROLLING METHOD - A turbine engine includes a plurality of variable fan inlet guide vanes. Where the turbine engine is a tip turbine engine, the variable fan inlet guide vanes permit the ability to control engine stability even though the fan-turbine rotor assembly is directly coupled to the axial compressor at a fixed rate. The fan inlet guide vanes may be actuated from an inner diameter of the fan inlet guide vanes. | 06-16-2011 |
