Portuguese 
English 
Spanish 
3 min of reading 
0 comments 
New Chinese Hypersonic Engine Increases Efficiency and Feasibility of Traveling at Extremely High Speeds
Researchers in China have introduced an innovative concept for hypersonic engines, combining detonation and ramjet technologies to create a more efficient engine. A team from Tsinghua University in Beijing developed the Ram-Rotor Detonation Engine (RRDE), which integrates a detonation engine with a rotor compressor inspired by ramjets (a type of jet engine that has no moving parts).
This combination aims to provide continuous thrust and enhance overall performance in high-speed flights, overcoming the limitations of current engines.
Versatile Hypersonic Engine Design and Innovative Structure
The new design of the RRDE seeks to provide a more efficient and reliable propulsion cycle. Detonation, characterized by its rapid combustion, generates high pressures, compressing fuel and air with shock waves and releasing intense energy.
-
The end of Nokia: the brand that was the cellphone of an entire generation has ended its smartphones, left Brazil, and today survives only in basic phones in India while seeking a new partner.
-
Robots learn from dogs to understand human gestures and can now locate objects with 89% success.
-
In a tomb in the ancient Egyptian capital of Tanis, in the Nile Delta, archaeologists found 225 funerary figurines that were meant to serve the deceased in the afterlife.
-
AI promises to revolutionize the world, but its data centers could create an invisible toxic crisis: a study by Nature estimates up to 5 million tons of electronic waste by 2030, with servers, GPUs, lead, cadmium, and rare metals that global recycling still cannot absorb.
This concept is an evolution compared to pulsed detonation engines (PDE) and rotating detonation engines (RDE), which face challenges in maintaining constant thrust under practical conditions.
How Does the RRDE Work?
The RRDE utilizes rotating blades that compress, ignite, and expand gases continuously. Inspired by sheep rotor compressors, it allows for the stabilization of shock waves, optimally increasing pressure and thrust.
The structure of the RRDE includes a rotor with helical blade patterns, housed in a stationary shell. As fuel and air pass through the channels between the blades, extension, interference, and expansion occur in a compact system.
Key Benefits of the RRDE
- Continuous and Stable Operation: The design allows for continuous detonations and results, providing high pressure and efficiency.
- Speed Flexibility: Capable of operating at different speeds, the RRDE adapts to rotor speed, making it more versatile.
- Reduction of Disruptive Shocks: Minimizes the formation of disturbing shock waves, ensuring enhanced performance.
This system differs from intended detonation engines by offering more reliable propulsion, capable of operating at low starting speeds.
For hypersonic aircraft, the RRDE represents a significant advancement, given that previous engines, such as the oblique detonation engine and the pulsed detonation engine, were not as effective.
Test Results and Impact on RRDE Performance
The tests conducted allowed the RRDE to achieve combination, fusion, and expansion processes in a single rotor. It utilizes a fixed detonation wave relative to the rotor, increasing pressure and efficiency, highlighting the current systems.
The RRDE operates smoothly at various speeds, simplifying the combustion process. The main factors determining engine performance are the relative inlet velocity (V0), the absolute inlet velocity, and the fuel-air ratio (ϕ).
Challenges and Limitations Faced
Despite the advantages, the development of the RRDE still faces challenges. Researchers have identified that maintaining stable detonation at lower speeds is a barrier to be overcome.
Protecting the blades from intense heat and the rotor’s durability at hypersonic speeds also pose difficulties for full engine predictions.
Numerical simulations have shown that the RRDE has the capability to stabilize detonation waves and adjust to various inlet configurations.
Practical tests using a hydrogen mixture provide a significant pressure increase, with a rise of 1.6. This performance is further strengthened by achieving injection speeds of up to Mach 4.2 and combustion gas temperatures close to 2,100 Kelvin (approximately 1,827 °C).
A team of Tsinghua researchers is committed to addressing the outstanding issues by exploring new materials and cooling methods that can enhance the RRDE design.
These advancements position the RRDE as a viable option for hypersonic propulsion, opening new possibilities for high-speed travel and aerospace applications.
Be the first to react!