Browse Topic: Fans

Items (403)
Test procedures are described for measuring noise at specific receiver locations (passenger and cargo doors, and servicing positions) and for conducting general noise surveys around aircraft. Procedures are also described for measuring noise level and directivity at noise source locations to facilitate the understanding and interpretation of the data. Requirements are identified with respect to instrumentation; acoustic and atmospheric environment; data acquisition, reduction and presentation, and such other information as is needed for reporting the results. This document makes no provision for predicting APU or component noise from basic engine characteristics or design parameters, nor for measuring noise of more than one aircraft operating at the same time. No attempt is made to suggest acceptable levels of noise or suitable subjective criteria for judging acceptability. ICAO Annex 16 Volume I Attachment C provides guidance on recommended maximum noise levels.
A-21 Aircraft Noise Measurement Aviation Emission Modeling
The oil cooling fan of a Main Gearbox (MGB) is a mechanically-driven component whose purpose is to force an air flow through an air cooled oil cooler; its performance is crucial in ensuring that the MGB oil temperature does not exceed a predefined threshold, set to alert the crew in case of an abnormal situation. The design and the certification of a cooling fan is a process involving several steps and multiple disciplines; mechanical design, aerodynamic analysis, dedicated tests carried out both on rigs and at aircraft level need to be exploited as complementary tools to assess the correct aero-mechanical behavior of the system. The aerodynamic assessment is associated to performance, measured in terms of MGB oil temperature: considering a comparison between two cooling fans, one outperforms the other if the resultant MGB oil temperature is lower, keeping the same boundary conditions (engine torque, wind speed, ambient temperature, etc.). The correct mechanical behavior is instead
Sangiovanni, AndreaScaltritti, DiegoPodda, DanielePisani, PaoloSartori, SergioAlari, Lorenzo
The multi-role utility helicopter T625 GÖKBEY is designed by Turkish Aerospace and it is equipped with a pair of two-spool CTS800-4AT turboshaft engine developed by Light Helicopter Turbine Engine Company (LHTEC). Components of the cowlings, intakes and exhausts were designed with supplementing CFD analyses and performance of various alternatives were evaluated. Final designs were achieved based on the helicopter performance and engine limits. In order to verify the estimated engine installed performance in design phase, performance of the instrumented engine with its integrated equipment on the platform is examined using flight test data. This paper focuses on the CFD simulations based performance predictions of the air induction system, exhaust system, and IPS blower exhaust. A comprehensive study is assessed to create more realistic models by using flight test data.
Sancar, EmreEzertaş, Ahmet AlperBayat, AkayÇakıroğlu, TaylanDaldal, Abdurrahman Burak
The current work focuses on understanding the aerodynamics of a single and coaxial rotor in hover subjected to 1-minus-cosine gust profiles. The work was performed using an in-house free-vortex method that includes the contribution of unsteady aerodynamic terms using the Duhamel integral. Studies were conducted on the Harrington single and coaxial rotor systems trimmed to CT /σ = 0.1, with the gust duration varying from 1-50 revolutions of the rotor, i.e., 0.3 - 15 seconds. Gust amplitudes were also varied from 0.1ωR-0.3ωR. Results were analyzed in terms of the deviation of thrust from the hover values, the frequency content of this signal, angle of attack variations across the span, and the structure of the wake as the system goes through the gust event. It was noted that for single and coaxial rotors, edgewise gusts result in higher frequency components being present in the thrust compared to the axial gust. Large changes in the angle of attack were observed, which could potentially
Narayanan, ShrivathsanGovindarajan, BharathChandel, Aaditya
The use of converging-diverging (C-D) variable area nozzle (VAN) in military aeroengines is now common, as it can give optimal expansion and control over engine back pressure, for a wide range of engine operations. At higher main combustion temperatures (desired for supercruise), an increase in the nozzle expansion ratio is needed for optimum performance. But changes in the nozzle throat and exit areas affect the visibility of engine hot parts as the diverging section of the nozzle is visible for a full range of view angle from the rear aspect. The solid angle subtended by engine hot parts varies with change in visibility, which affects the aircraft infrared (IR) signature from the rear aspect. This study compares the performances of fixed and variable area nozzles (FAN and VAN) in terms of engine thrust and IR signature of the engine exhaust system in the boresight for the same increase in combustion temperature. This study is performed for two cases: (i) variable throat area and
Baranwal, NidhiMahulikar, Shripad P.
This SAE Standard applies to self-propelled sweepers and scrubbers as defined in SAE J2130-1 and J2130-2.
MTC2, Sweeper, Cleaner, and Machinery
As embedded electronic control systems are increasingly penetrating vehicle subsystems, the designers are faced with a dilemma of providing state of art vehicle features on one hand and ensuring frugal implementation of the same to meet competitive pressures on the other. For embedded software and hardware systems this means adoption of judicious and innovative design choices with reusable building blocks. This paper dwells upon various design aspects of control and monitoring which are frequently used for automotive applications such as feed-forward and proportional integral control, diagnostics for sensor boundary conditions, handling of intermittent faults without causing nuisance to the vehicle users etc.
Vaidya, Vishwas Manohar
The effects of key design parameters of tilting distributed ducted fans are investigated through steady-state CFD simulations to assess the benefits of using variable geometry ducts in urban air mobility applications. The analysis is made on three adjacent ducted fans mounted at the trailing edge of a semi-span wing. The fans are represented by body forces calculated using the blade element theory. The duct expansion ratio, the duct thickness and the fan design expansion ratio are varied along with the fan speed, the crosswind speed in hover and the airspeed in forward flight. For each combination of the parameters, the hover Figure of Merit and crosswind stall speed as well as the forward flight lift coefficient, thrust coefficient and propulsive efficiency are evaluated. From these results, variable geometry ducted fans are benchmarked against fixed geometry ducted fans using a simplified 1 hour mission with 10% of hover time. It is found that a ducted fan equipped with a Krueger
Marois, FrancisPicard, MathieuRancourt, David
State-space inflow models have long been the standard for rotor wake modeling for flight dynamics and control simulation. As rotorcraft design continues to trend toward Future Vertical Lift (FVL) multi-rotor configurations in order to overcome the limitations of traditional design, the use of state space inflow models must similarly evolve to capture the complex aerodynamic interactions inherent to these new rotorcraft configurations. There is a demand for a state-space inflow model that accurately captures the significant aerodynamic interactions that occur between multiple rotors, ducted fans, wings, and complex airframes that preexisting inflow formulation fails to address. This paper discusses the ongoing effort to establish a robust methodology for deriving a state-space inflow model suitable for FVL applications from first-principle based viscous Vortex Particle Method (VPM) using the CIFERR system identification tool. The paper focuses on areas of enhancement that expand the
Gladfelter, MatthewTischler, MarkJuhasz, OndrejHe, ChengjianChang, ChongseokJ., Mark
Items per page:
1 – 50 of 403