Browse Topic: Pumps
The purpose of this aerospace information report is to provide a listing of national and international metric standards for use in aerospace fluid systems with their equivalent SAE inch, International ISO, and European AECMA standards.
This SAE Recommended Practice sets forth a method for evaluating the flow properties of automotive sealers that have been dispensed via a high pressure automatic system.
High speed rotorcraft transmissions are subject to load-independent power losses consisting of drag and pumping loss. Tightly conforming shrouds enclosing the transmission gears are often incorporated to reduce the drag component of the total load independent losses. However, tightly conforming axial shrouding can result in an increase in the pumping loss component. Quantifying the pumping loss of shrouded gear transmissions has been the subject of many studies. This study presents a new approach for estimating pumping loss based on the concept of swept volume borrowed from the positive displacement pump and compressor industry. In this study, pumping loss of shrouded gear transmissions is considered to be related to the swept volume of the gear sets and the downstream flow resistance created by the shroud clearances. The drag loss and pumping loss of a spur gear pair have been determined through testing using the NASA Glenn Research Center Gear Windage Test Facility. The results from this testing have been compared to theoretical results using the formulations presented in this study. Good correlation exist between the test pumping power loss and the predicted pumping power loss for tightly conforming axial shroud configurations.
ABSTRACT Currently existing lead-lag dampers are complex and maintenance-intensive parts of the rotor hub, and they are ineffective solutions for stiff-inplane rotors which experience very small deformation at the blade root. This paper introduces a new class of rotor blade dampers that use Fluidic Flexible Matrix Composite (F2MC) tubes connected to fluidic circuits. Models are developed that couple the blade, F2MC tube, and fluidic circuit dynamics in order to assess the performance of the proposed solutions. In this paper, two different devices are proposed for augmenting the damping of hingeless and articulated rotors. The first device is a compact F2MC damped vibration absorber intended for stiff-inplane rotor applications. Simulation results predict that an F2MC absorber placed at the root of a representative stiff-inplane hingeless rotor blade can increase the blade damping ratio from 2% to over 6%. The second device provides lag damping in an articulated rotor blade by harnessing the blade lag motion to strain an F2MC tube that pumps fluid through an orifice into an accumulator. Damping ratios as high as 25% critical damping are predicted for a representative articulated blade, although the F2MC damper effectiveness varies greatly depending on the blade operating lag angle. As a precursor to future rotor testing, a prototype articulated blade F2MC damper is built and tested on a 4.85-foot radius rotor blade. Using this device, blade damping ratios of up to 14.3% are achieved on benchtop experiments which include simulated centrifugal loading.
ABSTRACT Hydraulic contamination is a major contributor to flight control anomalies, binding, and leakage of hydraulic components. Typically, filters are rated using Beta Ratio/Efficiency at certain micron sizes per standard lab tests such as ISO 16889 or Mil-F-8815D (Ref. 1, 2). These are all steady flow tests at 100°F. Unfortunately, during normal aircraft operations, hydraulic filters are exposed to a wide range of operating conditions such as high oil temperatures, vibration due to pressure pulsations and flight maneuvers, cyclic flow and thermal excursions. The current hydraulic filters used on Army helicopters tend to shed particles during cyclic flow and vibration which can cause close clearance spools to lock-up in servo controls. This may result in un-commanded flight control inputs. This can also result in low Mean Time Between Failures (MTBF) on pumps and actuators. The US Army has developed new hydraulic filter specifications which require dynamic test procedures using more realistic conditions. This has resulted in the development of more robust media filters, which have been shown during on-aircraft demonstrations to increase fluid cleanliness and decrease maintenance costs.
ABSTRACT Retreating Side Blowing (RSB) is a concept to blow air through the blade to suppress dynamic stall on the retreating side of the rotor, and enhance a vehicle's flight envelope at high speed and high loading forward flight conditions. Passive RSB utilizes a rotating blade as a centrifugal pump to drive flow from the inlet at the root to the outboard region. Current numerical studies examined the effectiveness of RSB in conjunction with validation against wind-tunnel measured data at high advance ratio conditions. The impact of varying freestream velocity on the performance of a blown pitching airfoil was also examined using two-dimensional airfoil calculations. The variation and timing of the freestream velocity significantly decreased the stall suppression benefit of a blown airfoil versus a fixed freestream. The validation of three-dimensional rotor simulations showed good correlation with measured data in predictions of integrated performance, section loading, and duct flow properties. Both measured data and numerical simulation showed no significant performance benefit from RSB in the tested flight conditions. Detailed examination indicated the RSB was able to reduce retreating side separation, but pumping torque, geometric modification due to slots, and increased retreating side horizontal force overwhelmed the retreating side torque benefit. Additional numerical explorative studies showed that powered-blowing could achieve significant performance improvement from pure aerodynamic perspective. However, the additional blowing power cancelled out most of benefit. An inlet valve model for simulation of scheduled blowing was also studied, but meaningful benefit was not observed. The retreating side blowing was able to reduce aerodynamic sources of retreating side vibration torsional load. However, the peak blade torsional load emerged on the advancing side at high advance ratio conditions.
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