| Patent application number | Description | Published |
|---|
| 20080201008 | System and method for an integrated additive manufacturing cell for complex components - An integrated additive manufacturing cell (IAMC) that combines conventional manufacturing technologies with additive manufacturing processes is disclosed. Individual IAMCs may be configured and optimized for specific part families of complex components, or other industrial applications. The IAMCs incorporate features that reduce hardware cost and time and allow for local alloy tailoring for material properties optimization in complex components. | 08-21-2008 |
| 20080304958 | GAS TURBINE ENGINE WITH AIR AND FUEL COOLING SYSTEM - A gas turbine engine is provided with a first heat exchanger associated with a cooling air flow to deliver cooling air to a turbine section. A second heat exchanger is associated with a fuel supply line for delivering fuel into a combustion section. An intermediate fluid cools air at the first heat exchanger and heats fuel at the second heat exchanger. | 12-11-2008 |
| 20080310955 | Hybrid cooling of a gas turbine engine - A hybrid cooling system for a gas turbine engine includes a vapor cooling assembly and a cooling air cooling assembly. The cooling air cooling assembly is configured to remove thermal energy from cooling air used to cool a first component of the gas turbine engine. The 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. The vaporization section is located at least partially within a second component of the gas turbine engine, and the condenser section is located outside the second component. | 12-18-2008 |
| 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 |
| 20090107109 | Variable bypass turbine fan - An engine for powering a vehicle, such as a military aircraft or a commercial aircraft, is provided. The engine broadly comprises a main core with a plurality of spools with each spool having a plurality of compressor blades and a plurality of turbine blades attached thereto. One of the spools has a first set of fan blades attached thereto. The engine further has a variable bypass turbine fan formed by a second set of fan blades. The second set of fan blades is arranged outboard of the main core. The second set of fan blades may be decoupled from the first set of fan blades. | 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 |
| 20090142188 | SEAL ASSEMBLY FOR A FAN-TURBINE ROTOR OF A TIP TURBINE ENGINE - A seal assembly ( | 06-04-2009 |
| 20090145136 | TIP TURBINE ENGINE WITH MULTIPLE FAN AND TURBINE STAGES - A tip turbine engine ( | 06-11-2009 |
| 20090148272 | TIP TURBINE ENGINE AND OPERATING METHOD WITH REVERSE CORE AIRFLOW - A tip turbine engine ( | 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 |
| 20090148297 | FAN-TURBINE ROTOR ASSEMBLY FOR A TIP TURBINE ENGINE - A fan-turbine rotor assembly ( | 06-11-2009 |
| 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 |
| 20090232643 | Plurality of individually controlled inlet guide vanes in a turbofan engine and corresponding controlling method - 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. | 09-17-2009 |
| 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 |
| 20090235630 | NON-INTERRUPTED OIL SUPPLY FOR GAS TURBINE ENGINE - An oil supply system for a gearbox in a gas turbine engine includes a holding container which holds a quantity of oil to be delivered to a pump. The holding container includes a flexible barrier. | 09-24-2009 |
| 20090293496 | GAS TURBINE ENGINES GENERATING ELECTRICITY BY COOLING COOLING AIR - A portion of cooling air for cooling the turbine section of a gas turbine engine is tapped and passed through a heat exchanger. The portion of the cooling air is cooled in the heat exchanger, and the heat taken out of the portion of the cooling air is utilized to generate electricity. | 12-03-2009 |
| 20090297334 | GAS TURBINE ENGINE HAVING CONTROLLABLE INLET GUIDE VANES - An inlet guide vane assembly includes an active control feedback system and a plurality of inlet guide vanes. The inlet guide vanes are variable between a plurality of positions. Each of the plurality of inlet guide vanes is positioned in response to an output of the activate control feedback system. | 12-03-2009 |
| 20100263388 | Vapor cooled static turbine hardware - 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. | 10-21-2010 |
| 20100305742 | System and Method for an Integrated Additive Manufacturing Cell for Complex Components - An integrated additive manufacturing cell (IAMC) that combines conventional manufacturing technologies with additive manufacturing processes is disclosed. Individual IAMCs may be configured and optimized for specific part families of complex components, or other industrial applications. The IAMCs incorporate features that reduce hardware cost and time and allow for local alloy tailoring for material properties optimization in complex components. | 12-02-2010 |
| 20110056208 | REVERSED-FLOW CORE FOR A TURBOFAN WITH A FAN DRIVE GEAR SYSTEM - A gas turbine engine comprises a fan drive gear system, a low spool connected to the fan drive gear system, and a high spool disposed aft of the low spool. The low spool comprises a rearward-flow low pressure compressor disposed aft of the fan drive gear system, and a forward-flow low pressure turbine disposed aft of the low pressure compressor. The high spool comprises a forward-flow high pressure turbine disposed aft of the low pressure turbine, a combustor disposed aft of the high pressure turbine, and a forward-flow high pressure compressor disposed aft of the combustor. | 03-10-2011 |
| 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 |
