View source for 20240011637. TURBULENCE GENERATOR MIXER FOR ROTATING DETONATION ENGINE simplified abstract (Raytheon Technologies Corporation)

=TURBULENCE GENERATOR MIXER FOR ROTATING DETONATION ENGINE=


==Organization Name==

[[:Category:Raytheon Technologies Corporation|Raytheon Technologies Corporation]]


[[Category:Raytheon Technologies Corporation]]

==Inventor(s)==

[[:Category:Zhongtao Dai of West Hartford CT (US)|Zhongtao Dai of West Hartford CT (US)]][[Category:Zhongtao Dai of West Hartford CT (US)]]

[[:Category:Peter AT Cocks of South Glastonbury CT (US)|Peter AT Cocks of South Glastonbury CT (US)]][[Category:Peter AT Cocks of South Glastonbury CT (US)]]

==TURBULENCE GENERATOR MIXER FOR ROTATING DETONATION ENGINE - A simplified explanation of the abstract==


This abstract first appeared for US patent application 20240011637 titled 'TURBULENCE GENERATOR MIXER FOR ROTATING DETONATION ENGINE

==Simplified Explanation==

The abstract describes a combustor for a rotating detonation engine, which includes an outer wall and an inner wall that define an annular detonation chamber. The combustor has separate passages for fuel and oxidant, with the second passage arranged at an angle relative to the first passage to induce mixing of the flows.

* The combustor is designed for a rotating detonation engine.
* It includes an outer wall and an inner wall that define an annular detonation chamber.
* The inner wall is positioned within the outer wall.
* The combustor has separate passages for fuel and oxidant.
* The first passage feeds fuel and/or oxidant to the inlet.
* The second passage also feeds fuel and/or oxidant to the inlet.
* The second passage is arranged at an angle relative to the first passage.
* The angle of the second passage induces mixing of the flows from both passages.

Potential applications of this technology:
* Rotating detonation engines can be used in aerospace propulsion systems, such as aircraft engines and rocket engines.
* The improved mixing of fuel and oxidant in the combustor can enhance combustion efficiency and performance of the engine.
* The design of the combustor can potentially reduce emissions and improve fuel efficiency.

Problems solved by this technology:
* Traditional combustor designs may have issues with incomplete combustion, leading to lower efficiency and increased emissions.
* The separate passages and the induced mixing in this combustor design help to overcome these issues and improve combustion efficiency.

Benefits of this technology:
* Improved combustion efficiency can lead to increased performance and reduced fuel consumption.
* The design can potentially reduce emissions, contributing to environmental sustainability.
* The use of a rotating detonation engine can provide a compact and lightweight propulsion system for aerospace applications.


==Original Abstract Submitted==

a combustor for a rotating detonation engine includes a radially outer wall extending along an axis (a); a radially inner wall extending along the axis (a), wherein the radially inner wall is positioned within the radially outer wall to define an annular detonation chamber having an inlet for fuel and oxidant and an outlet; a first passage for feeding at least one of the fuel and the oxidant along a first passage axis (a) to the inlet; a second passage for feeding at least one of the fuel and the oxidant along a second passage axis (a) to the inlet, wherein the second passage axis is arranged at an angle (a) relative to the first passage axis whereby mixing of flow from the first passage and the second passage is induced.



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