Sonic Regulation Valve Layout for Stable Turbomachine Gas Flow
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Solution Overview
Problem
Existing angled flow valves in turbomachines suffer from instability and pressure losses, making it difficult to achieve a downstream/upstream pressure ratio greater than 0.8, which is critical for precise fluid management and mechanical stability.
Innovation Solution
A gaseous fluid control valve with an axial flow design featuring a reduced cross-sectional area, a movable valve member, and a guiding mechanism located downstream of the reduced cross-section, combined with a tapered obturator and guide pads for precise control and stability, ensuring fluid flow stability and minimizing pressure losses.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If angled flow valves are used for fluid control, then flow stability can be achieved at certain pressure ratios, but the system becomes more expensive and bulkier with reduced reliability
Solution Approach 1:
The patent inverts the conventional approach by positioning the guiding means downstream of the reduced cross-sectional area rather than upstream. This reversal allows the valve member to be self-guiding through the critical sonic flow zone, eliminating the need for complex upstream guidance mechanisms and achieving flow stability with a simpler design.
Solution Approach 2:
The patent extracts the guiding function from the upstream region and relocates it to the downstream region. By removing the guiding means from the critical flow convergence zone, the design achieves flow stability while reducing overall valve complexity and eliminating the need for multiple adjustment mechanisms.
2Measurement precision
If conventional valve designs are used to achieve flow control, then some level of stability can be obtained, but pressure losses increase and precision decreases
Solution Approach 1:
By inverting the position of the guiding means to downstream location, the valve member maintains precise alignment through the reduced cross-sectional area without requiring complex upstream guidance. This achieves superior flow control precision while minimizing pressure losses through streamlined flow paths.
Solution Approach 2:
The patent changes the geometric parameters of the flow channel, specifically creating a reduced cross-sectional area that induces sonic flow conditions. This parameter change enables precise flow control and reduces pressure losses by maintaining critical flow conditions where downstream pressure variations no longer affect upstream flow.
3Stability of the object's composition
If angled flow valves are employed, then fluid direction can be changed, but flow stability deteriorates and additional adjustments are required
Solution Approach 1:
The patent inverts the conventional valve design by placing the guiding means downstream, which allows the valve member to maintain stable alignment through the sonic flow zone without requiring complex adjustment mechanisms. This achieves inherent flow stability with simpler operation.
Solution Approach 2:
The valve member becomes self-guiding through the critical flow zone due to the downstream positioning of the guiding means. This self-service mechanism eliminates the need for external adjustment systems and achieves inherent flow stability without requiring operator intervention for maintenance of stability.
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 design achieves stable fluid flow with reduced pressure losses and improved precision, allowing for a downstream/upstream pressure ratio greater than 0.8, enhancing the reliability and efficiency of turbomachine systems.
Implementation Method 1
a reduced cross-sectional area to achieve a sonic velocity of the fluid
Implementation Method 2
flow stability is ensured by introducing sonic flow blocking, making the flow independent of the pressure downstream of the valve
Implementation Method 3
The curved portion of the channel allows the fluid to enter the axial portion progressively with a more uniform flow and minimal disturbances (no flow separation and reduced pressure losses)
Data Source
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AI summary
The invention relates to an aircraft turbomachine comprising a valve (1) for regulating a gaseous fluid, said valve (1) comprising: - a valve body (11) comprising a fluid flow channel (20), said channel (20) comprising an axial portion (25) extending along a main axis (200), said axial portion (25) having a zone (10) of reduced cross-section to obtain a sonic velocity of said fluid; - a valve member (13) movable in the flow channel (20) along said main axis (200), between an open position and a closed position in which the member (13) at least partially obstructs the flow of the fluid at the level of said zone (10) of reduced cross-section; - an actuator (12) for generating a displacement of the valve member (13) between the open position and the closed position; and - a guiding means (9) for guiding the movement of the valve member (13) in the channel (20);the channel (20) further comprising an inlet (6) in fluidic communication with said axial portion (25) by a curved portion (28); the guiding means (9) being located downstream of said zone (10) of reduced cross-section, along a direction of fluid flow during normal use of the valve (1).;