Author: Ronald H. Soeder
Publisher:
ISBN:
Category :
Languages : en
Pages : 58
Book Description
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.
Effect of Steady-state Pressure Distortion on Inlet Flow to a High-bypass-ratio Turbofan Engine
Author: Ronald H. Soeder
Publisher:
ISBN:
Category :
Languages : en
Pages : 58
Book Description
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.
Publisher:
ISBN:
Category :
Languages : en
Pages : 58
Book Description
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.
Effect of Steady-State Pressure Distortion on Inlet Flow to a High-Bypass-Ratio Turbofan Engine
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781725582958
Category :
Languages : en
Pages : 36
Book Description
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...
Publisher: Createspace Independent Publishing Platform
ISBN: 9781725582958
Category :
Languages : en
Pages : 36
Book Description
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...
Effect of Steady-state Temperature Distortion on Inlet Flow to a High-bypass-ration Turbofan Engine
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
Book Description
Effect of Steady-state Pressure Distortion on Flow Characteristics Entering a Turbofan Engine
Author: R. H. Soeder
Publisher:
ISBN:
Category :
Languages : en
Pages : 38
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 38
Book Description
Effect of Combined Pressure and Temperature Distortion Orientation on High-bypass-ratio Turbofan Engine Stability
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 40
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 40
Book Description
Performance of a Turbojet Engine in Combination with an External-internal-compression Inlet to Mach 2.88
Author: David N. Bowditch
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 34
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 34
Book Description
Scientific and Technical Aerospace Reports
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 652
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 652
Book Description
Engine Response to Distorted Inflow Conditions
Author:
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 320
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 320
Book Description
Monthly Catalogue, United States Public Documents
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1358
Book Description
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1358
Book Description
Monthly Catalog of United States Government Publications
Author: United States. Superintendent of Documents
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages :
Book Description
February issue includes Appendix entitled Directory of United States Government periodicals and subscription publications; September issue includes List of depository libraries; June and December issues include semiannual index
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages :
Book Description
February issue includes Appendix entitled Directory of United States Government periodicals and subscription publications; September issue includes List of depository libraries; June and December issues include semiannual index