Dual-Combustion Jet Engine With Adjustable Nozzles for Low-Speed Thrust
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Solution Overview
Problem
Existing aircraft jet engines, such as low-bypass turbofans with afterburners and ramjets, face high development and manufacturing costs, low specific impulse, short service life, and limited thrust at low speeds, necessitating more economical and efficient propulsion systems.
Innovation Solution
A jet engine design utilizing a gas generator to drive a turbine, incorporating two combustion chambers, adjustable nozzles, and dual fuel types, along with multiple operating modes including electric mode, to optimize thrust and efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If a conventional jet engine design is used, then the engine can operate, but it generates excessive noise and harmful exhaust emissions
Solution Approach 1:
The jet engine is divided into multiple independent combustion chambers instead of a single large chamber. Each combustion chamber operates independently with its own fuel injection and combustion process, allowing for better control of emissions and noise while maintaining overall thrust output
Solution Approach 2:
The exhaust nozzles of individual combustion chambers are nested within a common exhaust system. The exhaust gases from multiple chambers are combined and directed through shared nozzle structures, optimizing exhaust flow and thrust while reducing the overall engine footprint
2Object-affected harmful factors
If multiple combustion chambers are used to reduce emissions, then harmful factors decrease, but device complexity increases
Solution Approach 1:
The combustion chambers are designed with standardized, interchangeable components that can be replicated multiple times. Each chamber uses the same fuel injection system, combustion geometry, and cooling structures, allowing for mass production and simplified maintenance while achieving emission reduction through parallel operation
Solution Approach 2:
While individual combustion chambers are separate, their exhaust systems are merged into a common collection and discharge structure. This combining of exhaust flows from multiple chambers simplifies the overall nozzle configuration and reduces the number of separate exhaust paths needed
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 engine achieves reduced development and manufacturing costs, improved thrust across speed ranges, and enhanced operational flexibility, while maintaining efficient performance and adaptability.
Implementation Method 1
a first combustion chamber (121) arranged in series with a second combustion chamber (122), each combustion chamber (121, 122) having a fuel/oxidizer mixture combustion
Implementation Method 2
a convergent-divergent nozzle (141, 142, 143, 144) for each combustion chamber (121, 122), each nozzle (141, 142, 143, 144) having a supersonic exhaust jet
Data Source
Figure 1
Figure 2
Figure 3~4
AI summary
A jet engine for propelling aircraft, capable of providing thrust from rest to high speeds. Characterised in that it employs a liquid oxidant and two liquid fuels of different molecular weights. The engine has an axial compressor (16) or several axial compressors located on the same plane, but differs from a conventional gas turbine in that the turbine is driven by a gas generator. At the outlet of the turbine there is a gasification chamber (23) into which more fuel is injected. Combustion of the gases from the gasification chamber is performed in two combustion chambers (18) with a rectangular cross-section, separated by a central body (10). The exhaust of the gases is performed in nozzles with a square convergent/divergent cross-section (19) and (21). The cross-section of the throats (26) can be adjusted by means of two mobile elements (20). The final section of the central body (10) forms a wedge-shape (27), enabling the continued expansion of the exhaust gases.