Aircraft Engine Hydraulic Transfer Assembly for Rotating Actuator Supply
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Solution Overview
Problem
Existing aircraft engine turbomachines face challenges in efficiently supplying fluid to hydraulic actuators for variable pitch vane control, leading to high electrical power consumption, large engine size, and potential irreversible damage to pumps at high speeds.
Innovation Solution
A hydraulic assembly comprising a pump with a stationary casing and a hydraulic transfer unit that includes a transfer block and an envelope, allowing fluid to be transferred from the pump to a rotating hydraulic actuator without the need for a rotating electrical transformer.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a rotating electrical transformer and rotating pump are used to supply fluid to the hydraulic actuator, then the fluid supply function is achieved, but the electrical power consumption increases and the size and weight of the module increase
Solution Approach 1:
Instead of rotating the pump with the actuator, the invention inverts the approach by keeping the pump stationary and rotating the hydraulic transfer unit. The pump is driven by an electric motor in a stationary frame, while the hydraulic transfer unit rotates with the actuator to deliver fluid. This inversion eliminates the need for a rotating electrical transformer and reduces electrical power consumption.
Solution Approach 2:
The system is segmented into two independent parts: a stationary pump unit driven by an electric motor, and a rotating hydraulic transfer unit that interfaces with the actuator. This segmentation allows the pump to remain in a stationary frame where electrical power consumption is minimized, while the transfer unit handles the rotating fluid delivery function.
2Reliability
If a rotating electrical transformer and rotating pump are used, then fluid supply to the actuator is enabled, but the size and weight of the engine module increase
Solution Approach 1:
The invention inverts the conventional arrangement by keeping the heavy pump and electric motor in a stationary position rather than rotating them with the actuator. The rotating component is reduced to only the hydraulic transfer unit, which is lighter. This significantly reduces the overall weight and size of the engine module while maintaining reliable fluid supply.
Solution Approach 2:
The heavy electrical components (electric motor and pump) are extracted from the rotating assembly and placed in a stationary frame. Only the essential hydraulic transfer function remains in the rotating unit, reducing the weight and size of the moving parts in the engine module.
3Productivity
If the pump is rotated at high speeds with the module, then fluid supply is maintained, but the pump suffers irreversible damage
Solution Approach 1:
The invention inverts the rotational arrangement by keeping the pump stationary and allowing only the hydraulic transfer unit to rotate with the module. This ensures the pump operates in a stationary frame without experiencing high-speed rotation damage, while fluid supply continuity is maintained through the rotating transfer unit that delivers hydraulic fluid to the moving actuator.
Solution Approach 2:
The stationary pump uses hydraulic fluid as an intermediary to transfer energy to the rotating actuator through the hydraulic transfer unit. This allows the pump to remain stationary and durable while still providing continuous fluid supply to the rotating components through the hydraulic medium.
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
This solution reduces the size and weight of the turbomachine module, eliminates the need for bulky electrical transformers, and ensures reliable fluid supply to the hydraulic actuator, while minimizing the risk of pump damage at high speeds.
Implementation Method 1
a pump (54) comprising a casing (54a) and a rotor (54b) arranged inside the casing, the casing having at least one hydraulic pipe (540) for the passage of a fluid
Implementation Method 2
an envelope (56b) which covers the transfer block (56a) and which is guided in rotation about an axis of revolution and about the transfer block, the envelope having a fluid outlet port (75, 76) which communicates with the internal channel (67, 68)
Data Source
AI summary
A hydraulic assembly for an aircraft engine includes a pump with a housing and a rotor arranged inside the housing. The housing has at least one hydraulic line configured for the passage of a fluid; and a hydraulic transfer unit comprising: a hydraulic transfer block attached to the housing and comprising an internal fluid passage channel which communicates with the hydraulic line, and a casing which covers the transfer block and which is guided in rotation about an axis of revolution (Y) and about the transfer block, the casing having a fluid outlet port that communicates with the internal channel.