Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781725032620
Category :
Languages : en
Pages : 34
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Flow angle, static-pressure, and total-pressure distributions were measured in the passage ahead of a turbofan engine operating with inlet pressure distortion. Distortions were generated with five screen configurations and one solid plate configuration. The screens and solid plate were circumferential and mounted on a rotatable assembly. Reynolds Number Index upstream of the distortion device was maintained at 0.5, 0.35, or 0.2, and engine corrected low-rotor speeds were held at 6000 rpm and 8600 rpm. Near the engine inlet, flow angle was largest at the hub and increased as flow approached the engine. The magnitude of static-pressure distortion measured along the inlet-duct and extended bullet nose walls increased exponentially as the flow approached the engine. Wall static-pressure distortion was also a function of distortion harmonic. Soeder, R. H. and Bobula, G. A. Glenn Research Center NASA-TM-79134, E-9982, AVRADCOM-TR-79-19 ...
Author: R. H. Soeder
Publisher:
ISBN:
Category :
Languages : en
Pages : 38
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Author: Ronald H. Soeder
Publisher:
ISBN:
Category :
Languages : en
Pages : 58
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Experiments were conducted to determine the effects of steady-state circumferential-pressure distortion on inlet flow and internal engine performance of a high-bypass-ratio turbofan engine. To measure these effects, flow-angle, static-pressure, and total-pressure instrumentation was placed between the rotatable distortion-generator assembly and the engine inlet. In addition, both static-pressure and total-pressure were recorded at the fan exit and compressor inlet and exit. Three circumferential screens were separately mounted on the rotatable assembly. For all configurations data were recorded at each of twelve 30 deg increments of assembly rotation. Experiments were conducted with fan speeds (corrected to station 2 temperature) of 80 or 90 percent of rated condition (7005 rpm) and Reynolds number indices of 0.2 or 0.5. Yaw angle increased between the distortion-generating assembly and the engine inlet. A change in Reynolds number index (RNI) has only a slight effect and a change in speed had no effect on yaw angle distribution. The flow angle was largest in the hub region of the engine inlet.
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781725175860
Category :
Languages : en
Pages : 36
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Static pressure and total pressure distributions were measured in the inlet duct upstream of the engine inlet and within the fan and compressor of a YTF34 turbofan engine. In addition, the free stream flow angle was measured between the distortion generator and the engine inlet. Distortions were generated using three screen configurations with extents of 90 deg or 180 deg. The screens were mounted on a rotatable screen assembly. Reynolds number index upstream of the distortion device was maintained at 0.5 or 0.2, and engine fan speed corrected to station 2 temperature was maintained at 80 or 90 percent of rated condition (7005 rpm). Flow angle was nearly constant near the distortion device and increased as flow approached the engine inlet. The largest flow angle occurred in the hub region of the engine inlet. Static pressure distortion along the inlet duct increased exponentially as the flow approached the engine. Both static pressure and total pressure distortions were attenuated between engine inlet and compressor exit. Soeder, R. H. and Bobula, G. A. Glenn Research Center NASA-TM-82964, E-1383, NAS 1.15:82964, AVRADCOM-TR-81-C-27 RTOP 505-32-6A...
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1028
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Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
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Category : Airplanes
Languages : en
Pages : 320
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Category :
Languages : en
Pages : 36
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Category :
Languages : en
Pages : 48
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Category :
Languages : en
Pages : 40
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Category :
Languages : en
Pages : 942
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