Open Rotor Core Inlet Layout for Uniform Compressor Airflow
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Solution Overview
Problem
Traditional SRV configurations face challenges in balancing rotor aerodynamic design to maximize propulsive efficiency and uniform airflow into the core inlet, particularly at high angles of attack, leading to non-uniform flow and compressor instability.
Innovation Solution
Positioning the core inlet forward of the rotor allows the rotor root to pre-process air before entering the core, using a rotating frame and variable pitch mechanisms to control airflow, and incorporating a spinner to direct air into the core inlet without interference from rotor blades.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If the core inlet is located axially between the rotor blades and the static vanes in a traditional SRV configuration, then the rotor aerodynamic design can be simplified, but the airflow becomes non-uniform at high angles of attack leading to compressor instability
Solution Approach 1:
The patent moves the core inlet from a traditional axial position between rotor blades and static vanes to a forward position ahead of the rotor. This spatial repositioning in the axial dimension allows the rotor root to pre-process airflow before it enters the core inlet, creating more uniform airflow conditions at high angles of attack while maintaining simplified rotor aerodynamic design
Solution Approach 2:
By positioning the core inlet forward of the rotor, the rotor root acts as a preliminary airflow conditioning element before air enters the core. This preliminary action of the rotor root pre-processes the airflow, distributing it more uniformly and preventing compressor instability before the air reaches the core inlet
2Reliability
If the core inlet is positioned forward of the rotor with a rotating frame, then uniform airflow and compressor stability are improved, but the device complexity increases due to additional components
Solution Approach 1:
The rotating frame structure is designed to perform multiple functions simultaneously: it supports the rotor hub and rotor blades, enables variable pitch control through integrated mechanisms, and conditions airflow through the rotor root before it reaches the forward-positioned core inlet. This multi-functionality reduces the need for separate dedicated components for each function
Solution Approach 2:
The patent integrates the rotor hub support structure, variable pitch mechanism, and airflow conditioning function into a unified rotating frame assembly. By merging these functions into a single integrated structure rather than separate components, the overall device complexity is reduced despite the innovative forward core inlet positioning
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
Enhances propulsive efficiency by optimizing airflow distribution and stabilizing compressor operation, reducing blockage effects and improving thrust generation.
Implementation Method 1
the rotor root to pre-process air before entering the core, using a rotating frame and variable pitch mechanisms to control airflow
Data Source
AI summary
An aircraft propulsion system includes a rotor hub, rotor blades, a rotating frame, and a low-pressure compressor. The rotor hub is configured to rotate about a central axis. The rotor blades are arranged around the rotor hub. Each of the rotor blades is configured to rotate about a radial axis of the rotor hub. The rotating frame is positioned between the rotor hub and the plurality of rotor blades. The rotating frame is configured to allow air to pass without interference of the rotor blades. The low-pressure compressor is configured to receive the air passing through the rotating frame.