Centring Elements with Cooling Channels for Detonation Rocket Engine Thrust Symmetry

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Solution Overview

Problem

Rocket engines with annular combustion chambers and Aerospike nozzles experience thrust asymmetry due to the inability to achieve an ideal axisymmetric nozzle cross-section, leading to suboptimal performance and weight issues.

Innovation Solution

Incorporating evenly distributed centring elements with cooling channels in the detonation chamber and Aerospike nozzle to maintain a uniform critical cross-sectional area, ensuring constant distance between inner and outer walls, and providing additional cooling channels to protect against high temperatures.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Weight of moving object

If an Aerospike nozzle is used with an annular combustion chamber, then the engine weight is reduced and adaptability to external pressure is improved, but thrust asymmetry occurs due to inability to achieve ideal axisymmetric nozzle cross-section

Engineering Contradiction:

Improveengine weightVSAvoidthrust symmetry

Core Design Contradiction:

Weight of moving objectVSReliability

Solution Approach 1:

The outlet cross-section is divided into multiple segments by introducing centring elements that create distinct flow paths. These segments are evenly distributed around the annular chamber, allowing each to contribute to achieving axisymmetric thrust distribution while maintaining the compact Aerospike geometry.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Different regions of the nozzle outlet are given different geometric characteristics through the centring elements. The elements create localized flow control zones that compensate for the inherent asymmetry of the annular chamber, ensuring uniform thrust distribution across the entire outlet cross-section.

Inventive Principle:

Principle #3Local quality

2Ease of manufacture

If classic bell nozzles are used, then manufacturing is simpler, but the nozzle length becomes considerable and performance deteriorates in non-computational flight conditions

Engineering Contradiction:

Improvenozzle manufacturing simplicityVSAvoidnozzle length

Core Design Contradiction:

Ease of manufactureVSLength of moving object

Solution Approach 1:

The Aerospike nozzle design allows the outlet cross-sectional area to dynamically adapt to external pressure conditions. The centring elements with cooling channels enable the nozzle to maintain optimal performance across varying flight altitudes by adjusting the expansion characteristics of the exhaust flow, eliminating the need for long fixed-length bell nozzles.

Inventive Principle:

Principle #15Dynamics

3Reliability

If centring elements are added to maintain uniform cross-sectional area, then thrust symmetry is achieved, but the device complexity increases

Engineering Contradiction:

Improvethrust symmetryVSAvoidnozzle structure complexity

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

The centring elements serve multiple functions simultaneously: they maintain the uniform cross-sectional area of the nozzle outlet, provide structural support for the annular chamber, and act as cooling channel conduits to protect against thermal damage. This multi-functionality reduces the need for separate components, thereby limiting the increase in overall device complexity.

Inventive Principle:

Principle #6Universality (Multi-functionality)

Solution Approach 2:

The cooling channels are merged with the centring elements, combining the structural and thermal management functions into a single integrated component. This merging eliminates the need for separate cooling passages and simplifies the overall nozzle structure while maintaining thrust symmetry.

Inventive Principle:

Principle #5Merging (Combining)

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

This configuration eliminates thrust asymmetry by maintaining a uniform nozzle shape and prevents damage from exhaust gases, enhancing engine performance and reducing weight.

Implementation Method 1

the centring elements having cooling channels connected to one of the lines for supplying components of the propellant to the detonation chamber

Methodology Applied

Scientific EffectHeat transfer: Conduction (thermal)

Implementation Method 2

The use of cooling channels extending in the centring elements protects said elements against damage due to the high temperature of the exhaust gases leaving the detonation chamber

Methodology Applied

Scientific EffectThermal cooling: Cooling

Implementation Method 3

annular combustion chamber and an Aerospike nozzle... lines for supplying components of the propellant connected to the annular detonation chamber

Methodology Applied

Scientific EffectDetonation combustion: Detonation

Data Source

PatentUS11795891B2Detonation rocket engine comprising an aerospike nozzle and centring elements with cooling channels

Publication Date: 2023.10.24 SIEC BADAWCZA LUKASIEWICZ INSTYTUT LOTNICTWA

AI summary

The subject of the invention is a detonation rocket engine comprising an annular detonation chamber (5) connected to the Aerospike nozzle (4) and lines (2, 3) for supplying propellant components connected to the detonation chamber (5). The detonation chamber (5) has a bottom (9) connecting the inner wall (10) and the outer wall (11) between which the outlet (6) is formed. At the outlet (6) of the detonation chamber (5) there are at least three evenly distributed centring elements (1) connecting the inner wall (10) and the outer wall (11) of the detonation chamber (5), with cooling channels (7) connected to one of the lines (2, 3) supplying the propellant components to the detonation chamber (5).