Powerplant with multiple integrated gas turbine engines
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Solution Overview
Problem
There is a need for an improved multi-engine aircraft powerplant that enhances efficiency and adaptability across various flight conditions, particularly addressing subsonic and supersonic flight scenarios.
Innovation Solution
A powerplant design incorporating two gas turbine engines with integrated flow control systems that allow for the coupling of core and bypass flowpaths between engines, enabling modes of operation that optimize performance based on flight conditions, including a first mode for subsonic flight where the core flowpath is integrated with the second core flowpath and a second mode for supersonic flight where it is integrated with the second bypass flowpath.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If the first core flowpath is integrated with the second core flowpath during subsonic flight, then fuel efficiency is improved, but the system cannot accommodate higher temperature inlet air conditions
Solution Approach 1:
The flow control system dynamically reconfigures the flowpath connections between the two gas turbine engines based on flight conditions. During subsonic flight, the first core flowpath is connected to the second core flowpath for fuel-efficient operation. During supersonic flight, the system switches to connect the first core flowpath to the second bypass flowpath to handle higher temperature inlet air, allowing the system to adapt its configuration rather than being fixed
Solution Approach 2:
The flow control system provides multi-functionality by enabling the first engine to operate in multiple modes: it can be integrated with the second core flowpath during subsonic flight for efficiency, or with the second bypass flowpath during supersonic flight for temperature management. This universal design allows a single system to serve multiple operational requirements across different flight regimes
2Temperature
If the first core flowpath is integrated with the second bypass flowpath during supersonic flight, then the system can accommodate higher temperature inlet air, but fuel efficiency is reduced
Solution Approach 1:
The system dynamically switches flowpath configurations based on flight conditions. During supersonic flight when inlet air temperature is high, the flow control system connects the first core flowpath to the second bypass flowpath to manage thermal loads. This dynamic reconfiguration allows the system to prioritize temperature management over fuel efficiency when operating conditions require it
3Adaptability or versatility
If a flow control system is implemented to switch between different flowpath configurations, then adaptability across flight conditions is improved, but device complexity increases
Solution Approach 1:
The flow control system acts as an intermediary mechanism that manages the complex task of switching between different flowpath configurations. Rather than requiring complex mechanical reconfiguration of the entire engine system, the flow control system provides a dedicated control layer that simplifies the switching operation while enabling adaptability across different flight conditions
Data Source
AI summary
A powerplant is provided that includes a first gas turbine engine, a second gas turbine engine, a second engine bypass flowpath and a flow control system. The first gas turbine engine includes a first core flowpath fluidly coupled with a first inlet and a first exhaust. The first core flowpath extends sequentially through a first compressor section, a first combustor section and a first turbine section. The second gas turbine engine a second core flowpath fluidly coupled with a second inlet and a second exhaust. The second core flowpath extends sequentially through a second compressor section, a second combustor section and a second turbine section. The flow control system fluidly couples the first inlet and the first exhaust to the second core flowpath during a first mode. The flow control system fluidly couples the first inlet and the first exhaust to the second engine bypass flowpath during a second mode.