Coaxial Exhaust Nozzle Flaps for Thrust Vectoring Without Thrust Loss
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Solution Overview
Problem
Existing variable geometry exhaust nozzles in gas turbine engines face issues with undesirable changes in exit area and thrust vectoring when opposing flaps are moved asynchronously, leading to thrust loss or unintended vectoring.
Innovation Solution
The exhaust nozzle design features coaxially aligned first and second flaps with actuators that allow synchronized or differential angular rotation, enabling controlled thrust vectoring and variable geometry modes of operation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If opposing exhaust flaps are moved asynchronously to provide thrust vectoring, then thrust vectoring capability is improved, but exit area changes causing thrust loss occur
Solution Approach 1:
The exhaust nozzle is divided into multiple independently controllable flap segments (first flap, second flap, third flap, fourth flap) that can be actuated differently to achieve thrust vectoring while maintaining overall exit area. Each flap can be controlled independently to redirect exhaust flow without significantly changing the total exit area of the nozzle.
2Loss of energy
If opposing exhaust flaps are moved synchronously to maintain exit area, then thrust loss is minimized, but thrust vectoring capability is reduced
Solution Approach 1:
The exhaust nozzle employs dynamic control of multiple flaps where the first and second flaps can be actuated in opposition to each other, while the third and fourth flaps are actuated in opposition to the first and second flaps respectively. This dynamic configuration allows the system to maintain exit area while providing thrust vectoring capability through differential flap movement.
3Productivity
If variable geometry exhaust nozzle is used to maximize thrust production, then thrust efficiency is improved, but complexity of nozzle control increases
Solution Approach 1:
The complex variable geometry nozzle is segmented into multiple flaps (first, second, third, fourth flaps) that can be controlled in different configurations. This segmentation allows independent control of each flap to achieve various operational modes including thrust vectoring and exit area maintenance, managing the overall system complexity through modular control.
Data Source
AI summary
An exhaust nozzle for a gas turbine engine includes: an exhaust duct configured to receive an exhaust flow of gas from a combustor of the engine; a first flap rotatably coupled to the exhaust duct for rotation about a first axis; a first actuator configured to actuate the first flap about the first axis between a first inner and a first outer position; a second flap rotatably coupled to the exhaust duct for rotation about a second axis; and a second actuator configured to actuate the second flap about the second axis between a second inner and a second outer position. The first and second flaps at least in part define a passageway configured to convey the exhaust flow of gas to an exterior of the gas turbine engine. The first and second axes of rotation are coaxial. Also provides is a method of operating an exhaust nozzle.