Aircraft Engine
By setting the non-uniform pitch angle on the rotor assembly of the aircraft engine and adjusting the pitch of the rotor blades, the problem of lifting force requirements of existing aircraft during takeoff and landing is solved, and efficient lifting force enhancement effect is achieved, reducing the complexity and quality of the aircraft.
CN114109604BActive Publication Date: 2025-03-18GENERAL ELECTRIC CO
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Patent Information
- Application Number
- CN202111011578.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- Priority Date
- 2021-07-22
- Filing Date
- 2021-08-31
- Publication Date
- 2025-03-18
- Estimated Expiration
- 2041-08-31
AI Technical Summary
Technical Problem
The high lifting force devices of existing aircraft increase the complexity and quality of the aircraft, making it difficult to effectively solve the lifting force needs of the aircraft during takeoff and landing stages.
Method used
Using a distributed control system, the pitch of the rotor blade is adjusted by setting a non-uniform pitch angle on the rotor assembly of the aircraft engine to have different pitches at different locations to increase the air flow ratio at the top and bottom of the wing.
Benefits of technology
The lifting force generated by the wing under high lifting operation conditions is achieved, reducing the dependence on flaps and other lifting force devices, and reducing the complexity and mass of the aircraft.
✦ Generated by Eureka AI based on patent content.
Abstract
The present invention relates to an aircraft engine, and in particular to a method for operating an aircraft engine coupled to a wing of an aircraft, comprising: setting the pitch of a plurality of rotor blades of a rotor assembly of the aircraft engine at a non-uniform pitch angle along a circumferential direction of the aircraft engine, so that the plurality of rotor blades define a first pitch at a first position and a second pitch at a second position, wherein the second position is offset from the first position by 180 degrees, and wherein the first pitch is different from the second pitch.
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