System and method for control for unducted engine
a technology of unducted engine and control system, which is applied in the direction of rotors, machines/engines, other domestic objects, etc., can solve the problems of increasing the size and weight of the nacelle, general limited engine, and presenting technical challenges for the contra-rotating rotor assembly
Pending Publication Date: 2021-04-15
GENERAL ELECTRIC CO
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- Application Information
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Benefits of technology
The present invention has various benefits and advantages. These benefits can be found in the description of the invention or from practicing it.
Problems solved by technology
With such a configuration, the engine is generally limited in a permissible size of the bypass fan, as increasing a size of the fan correspondingly increases a size and weight of the nacelle.
Contra-rotating rotor assemblies however present technical challenges in transmitting power from the power turbine to drive the blades of the rotor assemblies rotating in opposing directions.
Method used
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[0024]Reference will now be made in detail to present embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to features in the drawings. Like or similar designations in the drawings and description have been used to refer to like or similar parts of the invention.
[0025]The word “exemplary” is used herein to mean “serving as an example, instance, or illustration.” Any implementation described herein as “exemplary” is not necessarily to be construed as preferred or advantageous over other implementations.
[0026]As used herein, the terms “first”, “second”, and “third” may be used interchangeably to distinguish one component from another and are not intended to signify location or importance of the individual components.
[0027]The terms “forward” and “aft” refer to relative positions within a gas turbine engine or vehicle, and refer to the normal operational attitud...
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A propulsion system is provided, the propulsion system including a variable pitch rotor assembly including a plurality of blades coupled to a disk. The plurality of blades includes a first blade configured to articulate a first blade pitch separately from a second blade configured to articulate a second blade pitch. A vane assembly is positioned in aerodynamic relationship with the variable pitch rotor assembly. A core engine including a high speed spool and a low speed spool, wherein the low speed spool is operably coupled to the rotor assembly. One or more controllers is configured to execute operations. The operations include articulating the first blade of the rotor assembly, wherein articulating the first blade alters the first blade pitch, and articulating the second blade of the rotor assembly, wherein articulating the second blade alters the second blade pitch.
Description
CROSS-REFERENCE TO RELATED APPLICATIONS[0001]This application is a non-provisional application claiming the benefit of priority under 35 U.S.C. § 119(e) to U.S. Provisional Application No. 62 / 915,364, filed Oct. 15, 2019, which is hereby incorporated by reference in its entirety.FIELD[0002]This application is generally directed to a turbomachine engine, including architectures for such an engine and methods for operating for such an engine.BACKGROUND[0003]A turbofan engine operates on the principle that a central gas turbine core drives a bypass fan, the bypass fan being located at a radial location between a nacelle of the engine and the engine core. With such a configuration, the engine is generally limited in a permissible size of the bypass fan, as increasing a size of the fan correspondingly increases a size and weight of the nacelle.[0004]An open rotor engine, by contrast, operates on the principle of having the bypass fan located outside of the engine nacelle. This permits th...
Claims
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IPC IPC(8): F02C9/22F01D7/00
CPCF02C9/22F01D7/00F05D2260/70F05D2240/24F05D2220/323F01D15/10F01D15/12F02C3/113F02C6/20F02C7/32F02C7/36F02K3/06F02K5/00F05D2220/325F05D2220/76F05D2240/60F05D2260/4023F05D2260/4031Y02T50/60B32B7/022B32B2307/558B32B2307/72B32B2307/732B32B2571/02B32B2605/18B64C1/12B64C1/38B64C2001/0072B64D27/12B64D45/00F01D5/146F01D5/187F01D5/30F01D5/3007F01D9/041F01D17/162F01D25/12F02C6/206F02C7/264F02C9/00F02K1/66F02K1/76F05D2230/60F05D2240/12F05D2250/37F05D2260/201F05D2260/30F05D2270/05F05D2270/051F05D2270/121F05D2270/304F05D2270/71F05D2270/81
Inventor ADIBHATLA, SRIDHARCAFARO, STEFAN JOSEPHMCQUISTON, ROBERT JON
Owner GENERAL ELECTRIC CO