Comprehensive Report of Fan Performance from Duct Rake Instrumentation on 1. 294 Pressure Ratio, 806 Ft/sec Tip Speed Turbofan Simulator Models PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Comprehensive Report of Fan Performance from Duct Rake Instrumentation on 1. 294 Pressure Ratio, 806 Ft/sec Tip Speed Turbofan Simulator Models PDF full book. Access full book title Comprehensive Report of Fan Performance from Duct Rake Instrumentation on 1. 294 Pressure Ratio, 806 Ft/sec Tip Speed Turbofan Simulator Models by National Aeronautics and Space Administration (NASA). Download full books in PDF and EPUB format.
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721151080
Category :
Languages : en
Pages : 150
Get Book Here
Book Description
A large scale model representative of an advanced ducted propulsor-type, low-noise, very high bypass ratio turbofan engine was tested for acoustics, aerodynamic performance, and off-design operability in the NASA Glenn 9- by 15-Foot Low-Speed Wind Tunnel. The test was part of NASA s Advanced Subsonic Technology Noise Reduction Program. The low tip speed fan, nacelle, and un-powered core passage were simulated. As might be expected, the effect of stall management casing treatment was a performance penalty. Reducing the recirculating flow at the fan tip reduced the penalty while still providing sufficient stall margin. Two fans were tested with the same aerodynamic design; one with graphite composite material, and the other with solid titanium. There were surprising performance differences between the two fans, though both blades showed some indication of transitional flow near the tips. Though the pressure and temperature ratios were low for this fan design, the techniques used to improve thermocouple measurement accuracy gave repeatable data with adiabatic efficiencies agreeing within 1 percent. The measured fan adiabatic efficiency at simulated takeoff conditions was 93.7 percent and matched the design intent. Jeracki, Robert J. Glenn Research Center WBS 22-781-30-50
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721151080
Category :
Languages : en
Pages : 150
Get Book Here
Book Description
A large scale model representative of an advanced ducted propulsor-type, low-noise, very high bypass ratio turbofan engine was tested for acoustics, aerodynamic performance, and off-design operability in the NASA Glenn 9- by 15-Foot Low-Speed Wind Tunnel. The test was part of NASA s Advanced Subsonic Technology Noise Reduction Program. The low tip speed fan, nacelle, and un-powered core passage were simulated. As might be expected, the effect of stall management casing treatment was a performance penalty. Reducing the recirculating flow at the fan tip reduced the penalty while still providing sufficient stall margin. Two fans were tested with the same aerodynamic design; one with graphite composite material, and the other with solid titanium. There were surprising performance differences between the two fans, though both blades showed some indication of transitional flow near the tips. Though the pressure and temperature ratios were low for this fan design, the techniques used to improve thermocouple measurement accuracy gave repeatable data with adiabatic efficiencies agreeing within 1 percent. The measured fan adiabatic efficiency at simulated takeoff conditions was 93.7 percent and matched the design intent. Jeracki, Robert J. Glenn Research Center WBS 22-781-30-50
Author: Robert J. Jeracki
Publisher:
ISBN:
Category :
Languages : en
Pages : 140
Get Book Here
Book Description
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781720522300
Category :
Languages : en
Pages : 64
Get Book Here
Book Description
A 1.294 pressure ratio, 725 ft/sec tip speed, variable pitch low noise fan was designed and tested in the NASA Glenn 9- by 15-foot Wind Tunnel. The design included a casing treatment that used recirculation to extend the fan stall line and provide an acceptable operating range. Overall aerodynamic experimental results are presented for this low tip speed, low noise fan without casing treatment as well as using several variants of the casing treatment that moved the air extraction and insertion axial locations. Measurements were made to assess effects on performance, operability, and noise. An unusual instability was discovered near the design operating line and is documented in the fan operating range. Measurements were made to compare stall margin improvements as well as measure the performance impact of the casing treatments. Experimental results in the presence of simulated inlet distortion, via screens, are presented for the baseline and recirculation casing treatment configurations. Estimates are made for the quantity of recirculation weight flow based on limited instrumentation in the recirculation system along with discussion of results and conclusionsFite, E. BrianGlenn Research CenterTURBOFANS; DISTORTION; DUCTS; EXTRACTION; AERODYNAMICS; LOW NOISE; FAN BLADES; PRESSURE RATIO; WIND TUNNELS; POSITION (LOCATION); TIP SPEED; SIMULATORS
Author: Brian E. Fite
Publisher: BiblioGov
ISBN: 9781289238926
Category :
Languages : en
Pages : 66
Get Book Here
Book Description
A 1.294 pressure ratio, 725 ft/sec tip speed, variable pitch low noise fan was designed and tested in the NASA Glenn 9- by 15-foot Wind Tunnel. The design included a casing treatment that used recirculation to extend the fan stall line and provide an acceptable operating range. Overall aerodynamic experimental results are presented for this low tip speed, low noise fan without casing treatment as well as using several variants of the casing treatment that moved the air extraction and insertion axial locations. Measurements were made to assess effects on performance, operability, and noise. An unusual instability was discovered near the design operating line and is documented in the fan operating range. Measurements were made to compare stall margin improvements as well as measure the performance impact of the casing treatments. Experimental results in the presence of simulated inlet distortion, via screens, are presented for the baseline and recirculation casing treatment configurations. Estimates are made for the quantity of recirculation weight flow based on limited instrumentation in the recirculation system along with discussion of results and conclusions.
Author: Demo J. Giulianetti
Publisher:
ISBN:
Category : Ducted fans
Languages : en
Pages : 56
Get Book Here
Book Description
Author: Ronald H. Soeder
Publisher:
ISBN:
Category :
Languages : en
Pages : 58
Get Book Here
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.
Author: James A. Schoenster
Publisher:
ISBN:
Category :
Languages : en
Pages : 32
Get Book Here
Book Description
Author: William T. Gorrell
Publisher:
ISBN:
Category : Impellers
Languages : en
Pages : 40
Get Book Here
Book Description
Detailed flow measurements made in the casing boundary layer of a two-stage transonic fan are summarized. These measurements were taken at stations upstream of the fan, between all blade rows, and downstream of the last blade row. At the design tip speed (429 m/sec) the fan achieved a peak efficiency of 0.846 at a pressure ratio of 2.471. The boundary layer data were obtained at three weight flows at the design speed: one near choke flow, one near peak efficiency, and one near stall. The data presented show steep axial velocity profiles at the stator exits were not as steep as those at the rotor exits. The data also show overturning of the flow at the tip at the stator exits. The effect of mixing is shown by the redistribution of the first-stage rotor-exit total temperature profile as is passes through the following stator.
Author: Richard P. Woodward
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 68
Get Book Here
Book Description
Author: Richard P. Woodward
Publisher:
ISBN:
Category : Lift fans
Languages : en
Pages : 116
Get Book Here
Book Description
