Aircraft Fuel Supply Circuit With Electromagnetic Pump Decoupling
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Solution Overview
Problem
Conventional turbomachines lack independent control of accessory pumps, such as fuel pumps, which are dependent on engine speed, leading to suboptimal fuel flow during startup and potential fuel recirculation.
Innovation Solution
Incorporation of an electromagnetic pump with a rotor and stator configuration, independent of the engine shaft, allowing for independent control of fuel flow and incorporating a one-way clutch for selective coupling with a centrifugal pump.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If the pump is mechanically coupled to the drive shaft, then the pump is driven by engine power, but the pump cannot be controlled independently of engine speed
Solution Approach 1:
The drive system is segmented into two independent parts: a centrifugal pump driven by the engine shaft and an electromagnetic pump driven by an independent electrical motor. This segmentation allows each pump to be controlled independently, with the electromagnetic pump able to operate at different speeds from the engine-driven centrifugal pump, thereby resolving the contradiction between independent control capability and system complexity.
2Productivity
If the pump speed is dependent on engine shaft speed, then the system is simple, but fuel flow rate cannot be optimized during startup
Solution Approach 1:
The fuel supply system incorporates two pumps with different drive mechanisms: the centrifugal pump provides fuel supply during normal engine operation, while the electromagnetic pump provides optimized fuel flow control during startup and idle conditions. This multi-functionality allows the system to optimize fuel flow for different operating conditions without excessive complexity, as each pump handles specific operational phases.
3Ease of operation
If an electromagnetic pump is added for independent control, then fuel flow can be controlled independently, but the device complexity increases
Solution Approach 1:
The electromagnetic pump acts as an intermediary device between the fuel tank and the centrifugal pump, particularly useful during startup when it primes the fuel system and controls fuel flow to the injector. This intermediary role allows independent fuel flow control without requiring complete redesign of the entire fuel system, thereby improving ease of operation while limiting the increase in overall system complexity.
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
Enables precise fuel flow control independent of engine speed, optimizing fuel supply and reducing recirculation, with a compact design that includes redundancy and energy generation capabilities.
Implementation Method 1
at least a plurality of coils distributed annularly inside the stator opposite the magnets
Implementation Method 2
the rotor is connected to the drive shaft by a one-way clutch element
Implementation Method 3
at least one centrifugal pump mechanically coupled to a drive shaft delivering mechanical power
Data Source
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AI summary
The invention relates to a fuel supply circuit of an aircraft engine, comprising a centrifugal pump which is mechanically coupled to a drive shaft (18) delivering a mechanical power. The circuit further comprises at least one electromagnetic pump (100) having at least one stator (110) which delimits an annular internal volume, in which a rotor (120) capable of driving a fluid is present, a plurality of magnets (130) which are distributed annularly around the rotor (120), and at least a plurality of coils (140) which are distributed annularly inside the stator (110) opposite the magnets (130). The rotor (120) is connected to the drive shaft (18) by means of a unidirectional clutch element (150).