Jet Engine with Rotating Disk Chamber for Variable Speed Operation
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Solution Overview
Problem
Current jet engines, such as pulsejet and ramjet engines, face limitations where pulsejet engines are prone to valve failure and ramjet engines can only operate at high speeds, necessitating the development of a jet engine capable of functioning at low speeds and beyond without heavy or complex mechanisms.
Innovation Solution
A jet engine design featuring a rotating disk chamber with a cylindrical air intake diffuser and combustion chamber, utilizing a gear system and intermittent actuation for fuel injection, allowing operation from stationary to hypersonic speeds through both continuous and discontinuous modes, with a hydraulic brake and pressurized air chamber for efficient speed adaptation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If a ramjet engine is used to propel aircraft, then the engine is inexpensive and easy to build, but the engine can only operate when aircraft exceed a minimum speed
Solution Approach 1:
The patent employs a rotating disk chamber that dynamically switches between continuous and discontinuous air passage modes. The disk rotates to alternately open and close air passages, enabling the engine to adapt its operation based on aircraft speed. This dynamic mechanism allows the engine to function at low speeds by creating discontinuous air flow, while maintaining simplicity in design.
Solution Approach 2:
The rotating disk chamber implements periodic action by cyclically opening and closing air passages during rotation. This periodic control of air flow enables the engine to operate in discontinuous mode at low speeds, where air is supplied in pulses rather than continuously, thereby extending the operating speed range without complicating the overall engine structure.
2Ease of manufacture
If a pulsejet engine is used to propel aircraft, then the engine is inexpensive and easy to build, but the engine breaks valves very easily after operating for a time
Solution Approach 1:
The patent extracts and eliminates the valve component from the traditional pulsejet engine design by introducing a rotating disk chamber that controls air passage through mechanical rotation rather than through valves. This removal of the valve component directly addresses the reliability issue while maintaining the inexpensive and easy-to-build characteristics of the engine.
Solution Approach 2:
The patent replaces the valve-based mechanical system with a rotating disk chamber mechanism. Instead of using valves to control air flow, the system uses a rotating disk with controlled passages, thereby eliminating the valve failure problem while maintaining simplicity in the mechanical design.
3Adaptability or versatility
If a turbojet engine is used to propel aircraft, then the engine can operate at all speeds, but the engine is heavy and complex
Solution Approach 1:
The patent segments the air intake system into distinct functional zones using the rotating disk chamber, which divides the air flow path into continuous and discontinuous passages. This segmentation allows the engine to achieve multi-speed operation capability while keeping each individual component simple and the overall mechanism lightweight compared to a turbojet.
Solution Approach 2:
The rotating disk chamber serves multiple functions: it controls air flow, regulates fuel injection timing, and enables both continuous and discontinuous operation modes. This multi-functionality allows the engine to operate across all speed ranges without requiring the complex separate systems of a turbojet, thereby reducing overall device complexity.
4Adaptability or versatility
If a heavy mechanism is used to enable low-speed operation, then the engine can operate at all speeds, but the engine becomes heavy and complex
Solution Approach 1:
The patent uses a lightweight rotating disk chamber that dynamically adjusts air flow patterns to enable low-speed operation. The disk rotates to create discontinuous air passages, providing low-speed capability without requiring heavy mechanical additions, thus maintaining the engine's lightweight characteristic while achieving versatility.
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
Enables aircraft to achieve hypersonic speeds without complex mechanisms and provides a simpler, lighter engine for subsonic flights with improved thrust-weight ratio, operating effectively from stationary to Mach 5 or faster.
Implementation Method 1
a rotating disk chamber located between the diffuser and the combustion chamber, which allows air to pass continuously or discontinuously from the diffuser to said combustion chamber
Implementation Method 2
the means of stopping the main shaft consist of a hydraulic brake connected to a brake disk that acts on said main shaft
Implementation Method 3
a pressurized air chamber with a compressor, connected to the main shaft by means of a second sliding crank and a second tie rod
Implementation Method 4
a combustion chamber with a spark plug and several fuel injection means
Implementation Method 5
a combustion chamber with a spark plug and several fuel injection means
Data Source
Figure 1
Figure 2
AI summary
A jet engine (1) with continuous and discontinuous impulse, which comprises a diffuser (2) with a cylindrical exterior shape, a combustion chamber (3), and several fuel injection means (19) and a nozzle (4), both with same exterior shape as the diffuser, a rotating disk chamber (5) that allows air to pass continuously or discontinuously from the diffuser (2) to the combustion chamber (3), an alternative engine with an alternative shaft (13) connected to a main shaft (9) of the engine (1) by means of a first cam (14), several means of stopping the main shaft (9), and a pressurized air chamber (16) connected to the main shaft (9), wherein the fuel injection means (19) are suitable for activating the injection in synchronization with the passage of air from the diffuser (2) to the combustion chamber (3).