Partial-Admission Turbine Control for Aircraft Waste Heat Recovery
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Solution Overview
Problem
Existing aircraft propulsion systems do not effectively utilize waste heat for enhancing mechanical energy generation, leading to inefficiencies in energy conversion and propulsion.
Innovation Solution
A partial-admission turbine assembly with a fluid regulator, heat exchanger, and control system to manage fluid flow and rotation speed, allowing for efficient energy transfer and maintenance within threshold ranges.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If waste heat is captured and used to generate mechanical energy, then energy conversion efficiency is improved, but system complexity increases
Solution Approach 1:
The partial-admission turbine assembly is integrated within the gas turbine engine structure, nesting the waste heat recovery system inside the existing propulsion system. The turbine stages are arranged concentrically with the engine core, and the fluid flow path is routed through existing engine components, thereby capturing waste heat without proportionally increasing overall system complexity
Solution Approach 2:
The fluid flow path serves multiple functions: it extracts work through the partial-admission turbine to generate mechanical energy, while also routing fluid between the heat exchanger and combustor. The system uses waste heat from the exhaust section to preheat or process fluid, thereby serving both propulsion and energy recovery functions through integrated fluid management
2Power
If corrected turbine inlet flow and rotation speed are maintained within threshold ranges, then mechanical energy generation is improved, but control system complexity increases
Solution Approach 1:
The controller continuously monitors corrected turbine inlet flow and corrected rotation speed, comparing these parameters against predetermined threshold ranges. Based on feedback from these measurements, the controller automatically adjusts fluid regulator positioning and heat exchanger operation to maintain optimal performance, thereby achieving stable mechanical energy generation through closed-loop control
Solution Approach 2:
The controller determines target positions for the fluid regulator and target operations for the heat exchanger in advance, based on desired corrected flow and rotation speed parameters. By pre-calculating control actions and executing them proactively, the system maintains optimal operating conditions without requiring complex real-time adjustments
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 system enhances energy conversion efficiency by maintaining corrected turbine inlet flow and rotation speed, improving mechanical energy generation and propulsion performance.
Implementation Method 1
a first heat exchanger, a partial-admission turbine sequentially form a portion of a fluid flow path through the assembly
Implementation Method 2
The partial-admission turbine includes a rotational assembly and a plurality of partial-admission turbine stages. The rotational assembly is mounted for rotation about a rotational axis of the partial-admission turbine
Implementation Method 3
The fluid regulator is configured to direct a fluid through the first heat exchanger and the partial-admission turbine along the fluid flow path
Data Source
AI summary
An assembly for an aircraft includes a fluid source, a first heat exchanger, a partial-admission turbine, a mechanical load, and a control assembly. The partial-admission turbine includes a rotational assembly and a plurality of partial-admission turbine stages. The rotational assembly includes a bladed turbine rotor. The bladed turbine rotor includes a plurality of rotor blade stages. Each of the plurality of partial-admission turbine stages includes a respective rotor blade stage of the plurality of rotor blade stages. The fluid source, the first heat exchanger, and the partial-admission turbine sequentially form a portion of a fluid flow path through the assembly. The mechanical load is coupled to the rotational assembly. The control assembly including a controller configured to determine a corrected turbine inlet flow and a corrected rotation speed for the partial-admission turbine, maintain the corrected turbine inlet flow within an inlet corrected flow threshold range, and maintain the corrected rotation speed within a corrected rotation speed threshold range.