Compound Engine Common Inlet for Nacelle Space Constraints
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Solution Overview
Problem
Existing compound engine assemblies used in aircraft, which incorporate a compressor as a supercharger or turbocharger, are often bulky and difficult to fit into existing aircraft nacelles, posing challenges in adapting them for aircraft applications.
Innovation Solution
A compound engine assembly is designed with a liquid-cooled heavy-fueled multi-rotor rotary engine core and a turbine section used as an exhaust energy recovery system, along with a compressor mounted in-line with the engine core, optimizing space and efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If a compound engine assembly with compressor and turbine section is installed in existing aircraft nacelles, then energy recovery and engine efficiency are improved, but the available space in the nacelle is insufficient due to the bulky assembly
Solution Approach 1:
The patent combines the compressor and turbine section into a single integrated compound engine assembly, merging previously separate functions into one compact unit. This integration allows the compressor inlet to be positioned at the same location as the turbine exhaust, enabling space-efficient installation within existing aircraft nacelles while maintaining both compression and energy recovery functions
Solution Approach 2:
The common inlet assembly serves multiple functions simultaneously: it acts as the inlet for both the compressor and the turbine section, and also functions as the exhaust outlet for the turbine. This multi-functional design reduces the number of separate components needed and minimizes the overall volume required for installation
2Use of energy by moving object
If separate inlets are provided for compressor and turbine section, then each component receives adequate airflow, but the device complexity and number of components increase
Solution Approach 1:
The common inlet assembly is designed to serve multiple purposes: it provides the inlet for the compressor, the inlet for the turbine section, and simultaneously acts as the exhaust outlet for the turbine. This single component performs what would traditionally require multiple separate inlets and associated hardware, thereby reducing device complexity while ensuring adequate airflow to both the compressor and turbine section
Solution Approach 2:
The patent merges the inlet functions for the compressor and turbine section into a single common inlet assembly. By combining these previously separate airflow paths into one unified structure, the design reduces the total number of components while maintaining proper airflow distribution to both the compressor and turbine section
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
The proposed engine assembly effectively addresses the space constraints of aircraft nacelles while enhancing engine efficiency through the integration of a rotary engine core, compressor, and turbine section, enabling efficient power generation and energy recovery.
Implementation Method 1
a turbine section (18) used as an exhaust energy recovery system
Implementation Method 2
a compressor (14) mounted in-line with the engine core (12)
Implementation Method 3
liquid cooled heavy fueled multi-rotor rotary engine core (12)
Data Source
Figure 1
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AI summary
A compound engine assembly including an air conduit 70 having an inlet 68 in fluid communication with ambient air around the compound engine assembly, a compressor 14 having an inlet in fluid communication with the air conduit, an engine core 12 including at least one rotary internal combustion engine and having an inlet in fluid communication with an outlet of the compressor, a turbine section 18 having an inlet in fluid communication with an outlet of the engine core and configured to compound power with the engine core; and at least one heat exchanger 72, 74 in fluid communication with the air conduit, each heat exchanger configured to circulate a fluid of the engine assembly in heat exchange relationship with an airflow from the air conduit circulating therethrough. A method of supplying air to a compound engine assembly is also discussed.