| Patent application number | Description | Published |
|---|
| 20080267762 | NACELLE ASSEMBLY HAVING INLET AIRFOIL FOR A GAS TURBINE ENGINE - A nacelle assembly includes an inlet lip section and an airfoil adjacent to the inlet lip section. The airfoil is selectively moveable between a first position and a second position to adjust the flow of oncoming airflow and to influence an effective boundary layer thickness of the nacelle assembly. | 10-30-2008 |
| 20080283676 | VARIABLE CONTRACTION RATIO NACELLE ASSEMBLY FOR A GAS TURBINE ENGINE - A nacelle assembly includes an inlet lip section having a highlight diameter and a throat diameter. One of the highlight diameter and the throat diameter is fixed and the other of the highlight diameter and the throat diameter is selectively adjustable in each of a first direction and a second direction relative to the inlet lip section to influence a contraction ratio associated with the inlet lip section. | 11-20-2008 |
| 20080286094 | VARIABLE GEOMETRY NACELLE ASSEMBLY FOR A GAS TURBINE ENGINE - A nacelle assembly includes an inlet lip section and a cowl section positioned downstream of the inlet lip section. At least a portion of the cowl section is moveable to influence an effective boundary layer thickness of the nacelle assembly. | 11-20-2008 |
| 20080298950 | NACELLE COMPARTMENT PLENUM FOR BLEED AIR FLOW DELIVERY SYSTEM - A gas turbine engine is provided with a nacelle having a hollow inner space. The inner space is utilized as a plenum for directing air from an inlet to an outlet at the upstream end of the nacelle to allow control of an effective lip width of the nacelle under certain flight conditions. | 12-04-2008 |
| 20080310956 | VARIABLE GEOMETRY GAS TURBINE ENGINE NACELLE ASSEMBLY WITH NANOELECTROMECHANICAL SYSTEM - A nacelle assembly includes an inlet lip section and a cowl section downstream of the inlet lip section. At least a portion of the cowl section is flexed to take various shapes through a nanoelectromechanical system and thereby influence an effective boundary layer thickness of the nacelle assembly. | 12-18-2008 |
| 20090003997 | VARIABLE SHAPE INLET SECTION FOR A NACELLE ASSEMBLY OF A GAS TURBINE ENGINE - A nacelle assembly includes an inlet section having a plurality of discrete sections. Each of the plurality of discrete sections includes an adaptive structure. A thickness of each of the plurality of discrete sections is selectively adjustable between a first position and a second position to influence the adaptive structure of each of the plurality of discrete sections. | 01-01-2009 |
| 20090008508 | VARIABLE CONTOUR NACELLE ASSEMBLY FOR A GAS TURBINE ENGINE - A gas turbine engine includes a compressor section, a combustor section, a turbine section and a nacelle assembly which at least partially surrounds the compressor section, the combustor section and the turbine section. At least a portion of the nacelle assembly includes an adjustable contour. The portion of the nacelle assembly including the adjustable contour is selectively moveable between a first portion and a second position to influence the adjustable contour of the nacelle assembly. A controller identifies an abnormal aircraft operating condition and selectively moves the portion of the nacelle assembly including the adjustable contour between the first position and the second position in response to detecting the abnormal aircraft operating condition. | 01-08-2009 |
| 20090110537 | Gas Turbine Engine Systems Involving Integrated Fluid Conduits - Gas turbine engine systems involving integrated fluid conduits are provided. In this regard, a representative engine casing for a gas turbine engine includes: a casing wall; and a fluid conduit integrated into the casing wall. | 04-30-2009 |
| 20090121083 | Nacelle Flow Assembly - A nacelle assembly for a turbine engine has a cowl for a turbine engine. The cowl has a first surface spaced from a second surface. The second surface defines defining a bypass flow passage. A flow volume is spaced between the first surface and the second surface. A plurality of holes are disposed on the cowl. Each of the plurality of holes are configured to alter local air pressure about one of the first surface and the second surface of the cowl. The plurality of holes are in communication with the flow volume. | 05-14-2009 |
| 20090235638 | VARIABLE AREA NOZZLE ASSISTED GAS TURBINE ENGINE RESTARTING - A turbofan engine starting system includes a core nacelle housing ( | 09-24-2009 |
| 20090252600 | ACTUATION OF A TURBOFAN ENGINE BIFURCATION TO CHANGE AN EFFECTIVE NOZZLE EXIT AREA - The invention relates to a turbine engine that includes a spool supporting at least one of a compressor and a turbine. A turbofan is coupled to the spool The spool is arranged in a core nacelle, and the turbofan is arranged upstream from the core nacelle. A fan nacelle surrounds the turbofan and the core nacelle and provides a bypass flow path. A structure extends radially between the core and fan nacelles to support the core nacelle relative to the fan nacelle. Surfaces are supported relative to the fixed structure and are moveable between closed and open positions to selectively obstruct bypass flow through the bypass flow path, thereby changing the effective area of the exit nozzle. A change in the effective area of the nozzle exit can be used to improve the efficiency and operation of the turbine engine. | 10-08-2009 |
| 20090259379 | REDUCED TAKE-OFF FIELD LENGTH USING VARIABLE NOZZLE - A turbofan engine control system and method includes a core nacelle housing ( | 10-15-2009 |
| 20100043390 | CONTROLLING ICE BUILDUP ON AIRCRAFT ENGINE AND NACELLE STATIC AND ROTATING COMPONENTS - A turbofan engine deicing system includes a core nacelle ( | 02-25-2010 |
| 20100269485 | INTEGRATED VARIABLE AREA NOZZLE AND THRUST REVERSING MECHANISM - A variable area fan nozzle for use with a gas turbine engine system includes a nozzle having a cross-sectional area associated with a discharge air flow from a fan bypass passage. The nozzle is selectively moveable between multiple static positions for varying the cross-sectional area and multiple thrust reverse positions that are different from the static positions for reversing a direction of the discharge flow from the fan bypass passage to produce a thrust reversing force. | 10-28-2010 |
| 20110020105 | NACELLE FLOW ASSEMBLY - A nacelle assembly for a turbine engine has a cowl for a turbine engine. The cowl has a first surface spaced from a second surface. The second surface defines defining a bypass flow passage. A flow volume is spaced between the first surface and the second surface. A plurality of holes are disposed on the cowl. Each of the plurality of holes are configured to alter local air pressure about one of the first surface and the second surface of the cowl. The plurality of holes are in communication with the flow volume. | 01-27-2011 |
| 20110072828 | GAS TURBINE ENGINE SYSTEM PROVIDING SIMULATED BOUNDARY LAYER THICKNESS INCREASE - A gas turbine engine system for an aircraft includes a nacelle having a fan cowl with an inlet lip section and a core cowl, at least one compressor and at least one turbine, at least one combustor between the compressor and the turbine, a bleed passage, and a controller. The bleed passage includes an inlet for receiving a bleed airflow and an outlet that discharges the bleed airflow in an upstream direction from the outlet. The controller identifies an operability condition and selectively introduces the bleed airflow near a boundary layer of the inlet lip section in response to the operability condition. | 03-31-2011 |
