Electrically Activated Fuel Pump for Helicopter Turboshaft Engines
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Solution Overview
Problem
Conventional helicopter turboshaft engines require manual fuel filling and priming during filter replacement, leading to increased maintenance time and immobilization of the aircraft, as the fuel pumps are tied to the engine shaft and cannot operate when stopped.
Innovation Solution
A fuel pumping module with a pump shaft connected to the turbine engine shaft and an electrical device that can drive the pump for priming and power generation, allowing independent activation of the fuel supply pump and decoupling from the engine shaft, enabling quick and reliable starting regardless of fuel levels.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If the fuel pump is mounted on the turbine engine shaft to deliver fuel flow as a function of shaft speed, then the fuel supply is automatically controlled during engine operation, but the pump cannot operate when the engine is stopped, requiring manual fuel filling during filter replacement
Solution Approach 1:
The pump shaft is separated from the turbine engine shaft, allowing the pump to be driven independently by an electrical motor during maintenance operations, while still being driven by the engine shaft during normal operation. This segmentation enables the pump to function in both manual and automatic modes without interference.
Solution Approach 2:
The pump shaft is designed to accept multiple driving sources: it can be driven by the turbine engine shaft during normal operation, or by an electrical motor during maintenance when the engine is stopped. This multi-functionality eliminates the need for manual fuel filling while maintaining automatic control during flight.
2Reliability
If a priming pump is added to fill the filter unit and supply pipeline with fuel during engine shutdown, then fuel can be supplied during maintenance, but the device complexity and mass of the helicopter increase
Solution Approach 1:
The existing fuel pump is made multi-functional by enabling it to operate in two distinct modes: automatic mode when driven by the engine shaft during flight, and manual mode when driven by an electrical motor during maintenance. This eliminates the need for a separate priming pump while maintaining fuel supply capability during both operation and maintenance.
Solution Approach 2:
The pump system serves itself by using the same pump mechanism for both automatic operation during flight and manual priming during maintenance, controlled by different driving sources. This self-service capability eliminates the need for additional dedicated priming equipment.
3Productivity
If the pump shaft is permanently coupled to the turbine engine shaft, then the pump is always driven at engine speed, but the pump cannot be activated independently for priming when the engine is stopped
Solution Approach 1:
The permanent mechanical coupling between the pump shaft and engine shaft is replaced with a decoupled configuration where the pump shaft can be independently driven by an electrical motor. This segmentation allows the pump to operate independently for priming while maintaining efficient engine-driven operation during flight.
Solution Approach 2:
The drive configuration is made dynamic, allowing the pump shaft to switch between being driven by the engine shaft during normal operation and being driven by an electrical motor during maintenance. This dynamic adaptability enables both high-productivity engine-driven operation and independent priming capability.
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
Reduces maintenance time by allowing fuel supply without manual filling and ensures reliable fueling during flight, decoupling the priming phase from the starting phase, and protecting the turbine engine by detaching the pump shaft when stopped.
Implementation Method 1
an electrical device which is mounted on said pump shaft and is adapted, according to a first mode of operation, to drive said pump shaft in rotation in order to actuate the supply pump
Implementation Method 2
a pump for supplying fuel to the turbine engine, mounted on said pump shaft and adapted to deliver a flow of fuel as a function of the speed of rotation of the turbine engine shaft
Data Source
AI summary
A turbine engine for an aircraft including a turbine engine shaft and a pumping module, including: a pump shaft, connected to the turbine engine shaft; a pump for supplying fuel to the turbine engine, mounted on the pump shaft, configured to deliver a flow of fuel as a function of a speed of rotation of the turbine engine shaft; and an electrical device mounted on the pump shaft and configured, according to a first mode of operation, to drive the pump shaft in rotation to actuate the supply pump and, according to a second mode of operation, to be driven in rotation by the pump shaft to supply electrical power to equipment of the turbine engine.