Circumferential Rotor Cooling Nozzle for Roundness-Controlled Assembly
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
The existing methods for cooling rotor stacks in gas turbine engines are inefficient, as natural cooling takes approximately 50% of the assembly time, and previous attempts to use fans have been unsuccessful in meeting the tight roundness and squareness requirements.
Innovation Solution
A cooling device with a circumferentially extending airflow nozzle, supported by adjustable rods, that directs uniform airflow to specific cooling locations, utilizing a manifold and airflow valves for precise control and monitoring with anemometers to accelerate the cooling process.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Manufacturing precision
If natural cooling is used for the rotor stack, then the roundness and squareness requirements are maintained, but the cooling time is excessively long (approximately 1 hour per cooling cycle, 50% of total assembly time)
Solution Approach 1:
The patent applies pneumatic cooling by directing controlled streams of cooling air onto the rotor stack using nozzles positioned around the assembly area. This forced convection cooling method replaces natural cooling, significantly reducing cooling time while maintaining precision through controlled airflow方向和强度
Solution Approach 2:
The cooling system uses multiple nozzles positioned at specific locations around the rotor stack to provide localized cooling where heat generation is highest. The airflow can be independently controlled for each nozzle, allowing precise temperature management at different areas of the assembly while preserving dimensional accuracy
2Loss of time
If fans are used to cool the rotor stack, then cooling time is reduced, but the roundness and squareness requirements are not met
Solution Approach 1:
Instead of using fans that create uncontrolled air movement, the patent employs directed pneumatic cooling through nozzles that deliver controlled air streams. This provides the cooling speed needed while preventing the excessive air flow that would disrupt the rotor stack's dimensional precision
Solution Approach 2:
The system applies cooling locally at specific points around the rotor stack rather than using general fan circulation. This localized approach ensures rapid heat removal without creating the strong, widespread air currents that fans produce, which would compromise the tight roundness and squareness tolerances
3Productivity
If the rotor stack is cooled rapidly, then assembly time is reduced, but the uniformity of cooling and dimensional precision may be compromised
Solution Approach 1:
The cooling system is segmented into multiple independent nozzles distributed around the rotor stack. Each nozzle can be controlled independently, allowing the system to achieve rapid overall cooling while maintaining uniform temperature distribution and dimensional precision through coordinated control of individual segments
Solution Approach 2:
By providing locally controlled cooling at multiple positions around the rotor stack, the system achieves uniform cooling across the entire assembly. Each nozzle targets specific areas, ensuring consistent temperature reduction throughout while preserving the tight dimensional tolerances required for assembly precision
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 significantly reduces the cooling time required for rotor assembly while maintaining the necessary roundness and squareness requirements, enhancing the efficiency of the assembly process.
Implementation Method 1
a compressed air source to supply an airflow to the airflow nozzle. The airflow nozzle may include a circumferential air nozzle that extends entirely around a circumference of the rotor assembly, and that is directed to deliver the airflow to a selected location
Data Source
Figure 1
Figure 2
Figure 3
AI summary
A cooling device (26) for a rotor assembly (10) of a gas turbine engine includes an airflow nozzle (28) configured to be installed at a cooling location of the rotor assembly (10). The airflow nozzle (28) extends entirely around a circumference of the rotor assembly (10) and includes a plurality of airflow inlets (44) and a nozzle outlet (32) to direct an airflow (34) toward the cooling location. An airflow source (40) is operably connected to the plurality of airflow inlets (44).