Hybrid Airbreathing Rocket Engine Module with Nested Compressor
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing hybrid airbreathing rocket engine modules are bulky and heavy due to non-uniform pressure drops across heat exchanger sections, necessitating mechanical flow-balancing solutions, which increases overall mass and reduces efficiency.
Innovation Solution
The engine module design places the compressor partially inside the inlet cone, with a reverse flow orientation, and positions the heat exchanger between the compressor and thrust chambers, achieving a uniform pressure drop across heat exchanger sections, eliminating the need for mechanical flow-balancing solutions and reducing the engine's overall length and mass.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If the compressor is arranged outside the inlet cone in prior art configurations, then the engine module has a longer length, but this results in non-uniform pressure drops across heat exchanger sections requiring mechanical flow-balancing solutions that increase mass
Solution Approach 1:
The compressor is nested within the inlet cone structure, with the compressor inlet positioned at the base of the inlet cone and the compressor housing contained within the cone's volume. This nesting arrangement eliminates the need for external flow-balancing mechanisms while maintaining compact dimensions, as the compressor integrates with rather than extends from the inlet cone.
2Manufacturing precision
If mechanical flow-balancing solutions such as turning vanes are implemented, then non-uniform pressure drops are compensated, but the overall mass of the engine module increases
Solution Approach 1:
The design replaces mechanical flow-balancing components (turning vanes, flow control mechanisms) with an optimized airflow path configuration. The compressor inlet positioning at the inlet cone base creates a natural flow distribution that achieves uniform pressure drops across all heat exchanger sections without requiring additional mechanical balancing devices, thereby reducing overall mass.
3Device complexity
If the compressor is positioned with its inlet end facing away from the heat exchanger arrangement, then the engine layout is simplified, but the pressure drop uniformity across heat exchanger sections deteriorates
Solution Approach 1:
Instead of positioning the compressor inlet away from the heat exchanger arrangement as in conventional designs, the inlet end of the compressor is inverted to face directly toward the inlet cone base where airflow enters. This reversed positioning optimizes the airflow path through the heat exchanger sections, ensuring uniform pressure drops are achieved across all sections while maintaining layout simplicity.
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 results in a more compact, lightweight engine module with improved mass flow distribution and reduced external aerodynamic forces, enhancing efficiency and reducing the need for mechanical flow control measures.
Implementation Method 1
an inlet cone configured to decelerate air received by the air intake arrangement
Implementation Method 2
a heat exchanger arrangement configured to pre-cool compressed air delivered by the compressor
Data Source
Figure 1A~1C
Figure 2
Figure 3
AI summary
A hybrid airbreathing rocket engine module (70) comprises an air intake arrangement (62) configured to receive air and a heat exchanger arrangement (63) configured to cool air from the air intake arrangement (62); a compressor (64) configured to compress air from the heat exchanger arrangement (63); and one or more thrust chambers (65). The air intake arrangement (62), the compressor (64), the heat exchanger arrangement (63), and the one or more thrust chambers (65) are arranged generally along an axis (69) of the engine module (70). The heat exchanger arrangement (63) is arranged between the compressor (64) and the one or more thrust chambers (65).