Multi-mode Overjet Engine with Duplex Turbine Guide Vane
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Solution Overview
Problem
Existing turbojet engines and afterburning turbojet engines face limitations in achieving higher thrust-to-weight ratios, which restrict aerospace vehicles from flying at higher speeds and altitudes.
Innovation Solution
The development of an Overjet engine capable of operating in Air Turbo Rocket (ATR) mode, along with conventional turbojet and afterburning modes, utilizing a Duplex Turbine Guide Vane (DTVG) and a turbine assembly to direct hot, fuel-rich gas from a gas generator onto the turbine blades, enhancing thrust and efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If an afterburner is added to a turbojet engine, then maximum thrust is significantly augmented, but thrust-to-weight ratio remains limited
Solution Approach 1:
The engine is designed to perform multiple functions by integrating both turbojet and air-turborocket modes within a single engine system. The turbine assembly can operate in conventional turbojet mode using compressor air, or switch to air-turborocket mode by directing gas generator exhaust onto the turbine blades, thereby achieving higher thrust-to-weight ratio without requiring separate engine systems
Solution Approach 2:
The invention changes the operational parameters of the turbine by allowing it to receive different energy sources: either hot gases from the combustor (conventional mode) or hot gases from the gas generator (air-turborocket mode). This parameter change enables the same turbine assembly to produce different thrust levels and efficiency characteristics based on flight requirements
2Weight of moving object
If an air-turborocket mode is implemented, then thrust-to-weight ratio and high speed flight capability are improved, but the ratio of thrust to propellant flowrate decreases
Solution Approach 1:
The engine system is made dynamic by enabling real-time switching between turbojet and air-turborocket modes based on flight conditions. The control system can adjust the gas generator operation and turbine airflow to optimize the thrust-to-propellant-flowrate ratio for specific mission requirements, allowing the system to adapt rather than being fixed in one operational mode
3Temperature
If a gas generator is added to enable ATR mode, then high altitude flight capability is improved, but device complexity increases
Solution Approach 1:
The invention merges the gas generator components with the existing turbojet engine system, integrating the oxidizer injection system, combustion chamber, and turbine interface into the conventional engine architecture. This consolidation reduces the overall complexity increase compared to adding a completely separate ATR system, as shared components are utilized across both operational modes
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
The Overjet engine achieves significantly higher thrust and improved altitude capabilities in ATR mode while maintaining fuel efficiency, with the ability to switch between modes to meet various flight requirements, and demonstrates twice the thrust of afterburning turbojets for the same air flowrate and compressor pressure ratio.
Implementation Method 1
A turbojet or afterburning turbojet with an ATR mode resembles its conventional counterpart, but with improved performance depending on the mode of operation
Implementation Method 2
a compressor powered by a turbine that is driven by the exhaust of a gas generator using a fuel rich liquid or solid propellant
Implementation Method 3
ram air compression is supplemented by a compressor powered by a turbine
Data Source
AI summary
A turbojet engine capable of operation in an Air Turbo Rocket (ATR) mode includes a compressor, a rotatable turbine wheel comprising turbine blades, a non-rotating guide vane ring comprising guide vanes, a turbine shaft configured to power said compressor, a combustor, a gas generator, and a main combustor. The main combustor is configured to combust hot, fuel rich gas from the gas generator in air compressed by the compressor. Hot, fuel rich gas from the gas generator is directed towards the turbine blades by a directing means.