Gas Turbine Nozzle Thrust Vectoring via Coanda and Fluidic Injectors
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing systems for manipulating flow fields, particularly in gas turbine engines, face limitations in effectively vectoring thrust at high pressure ratios, necessitating improved methods for directing exhaust flows.
Innovation Solution
A unique flow field manipulation system incorporating a nozzle with coanda and fluidic injectors that receive pressurized air from a compressed air subsystem, allowing for the vectoring of exhaust flows by influencing the exhaust stream with tangentially and perpendicularly flowing air, enabling control of thrust direction.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If existing flow field manipulation systems are used, then the system structure is relatively simple, but the ability to change thrust direction at high pressure ratios is insufficient
Solution Approach 1:
The flow field manipulation system is divided into multiple independent injector modules, each capable of controlling flow in specific directions. This segmentation allows the system to achieve complex thrust vectoring capabilities while maintaining modular simplicity in each individual component.
Solution Approach 2:
The injector system is designed to perform multiple functions: it can control primary flow, secondary flow, and tertiary flow simultaneously, and can operate across a wide range of pressure ratios. This multi-functionality enables a single system to adapt to various operating conditions without requiring separate specialized components.
2Productivity
If high pressure ratio operation is implemented, then thrust efficiency is improved, but the ability to vector thrust is reduced
Solution Approach 1:
The injector system incorporates dynamic control mechanisms that allow real-time adjustment of flow parameters including pressure ratio, flow direction, and mass flow rate. This dynamic capability enables the system to maintain optimal thrust efficiency while simultaneously achieving thrust vectoring across varying operating conditions.
Solution Approach 2:
The system utilizes multiple injectors that can independently vary flow parameters such as pressure ratio, mass flow rate, and injection timing. By changing these parameters dynamically, the system maintains high thrust efficiency while achieving effective thrust vectoring capability.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This system effectively vectors the exhaust flow by up to 10 degrees at high pressure ratios, providing enhanced control over aircraft movement and potentially supplanting traditional control surfaces, as demonstrated by computational studies.
Implementation Method 1
A first injector is a Coanda injector operable for delivering pressurized air into an interior of the nozzle
Implementation Method 2
A second injector is a fluidic injector operable for delivering pressurized air into an interior of the nozzle, wherein the second injector is located downstream of the first injector
Data Source
AI summary
In one embodiment, a nozzle of a gas turbine engine may be provided having a coanda injector and a fluidic injector which operate together to provide for a change in exhaust flow direction. The fluidic injector may be coincident with or downstream of the coanda injector and both may be used in high pressure ratio operations of the nozzle. The fluidic injector may be positioned opposite the coanda injector and, when activated, may provide for a region of separated flow on the same side of the nozzle as the fluidic injector. The coanda injector may provide additional momentum to an exhaust flow flowing through the nozzle and may encourage the flow to stay attached on the coanda injector side of the nozzle.