Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781720522300
Category :
Languages : en
Pages : 64
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
Fan Performance from Duct Rake Instrumentation on a 1. 294 Pressure Ratio, 725 Ft/sec Tip Speed Turbofan Simulator Using Vaned Passage Casing Treatment
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781720522300
Category :
Languages : en
Pages : 64
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
Publisher: Createspace Independent Publishing Platform
ISBN: 9781720522300
Category :
Languages : en
Pages : 64
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
Fan Performance from Duct Rake Instrumentation on a 1. 294 Pressure Ratio, 725 Ft/Sec Tip Speed Turbofan Simulator Using Vaned Passage Casing Treatment
Author: Brian E. Fite
Publisher: BiblioGov
ISBN: 9781289238926
Category :
Languages : en
Pages : 66
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.
Publisher: BiblioGov
ISBN: 9781289238926
Category :
Languages : en
Pages : 66
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.
Comprehensive Report of Fan Performance from Duct Rake Instrumentation on 1. 294 Pressure Ratio, 806 Ft/sec Tip Speed Turbofan Simulator Models
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721151080
Category :
Languages : en
Pages : 150
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
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721151080
Category :
Languages : en
Pages : 150
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
Comprehensive Report of Fan Performance from Duct Rake Instrumentation on 1.294 Pressure Ratio, 806 Ft/sec Tip Speed Turbofan Simulator Models
Author: Robert J. Jeracki
Publisher:
ISBN:
Category :
Languages : en
Pages : 140
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 140
Book Description
Wind-tunnel Test of a Full-scale, 1.1 Pressure Ratio, Ducted Lift-cruise Fan
Author: Demo J. Giulianetti
Publisher:
ISBN:
Category : Ducted fans
Languages : en
Pages : 56
Book Description
Publisher:
ISBN:
Category : Ducted fans
Languages : en
Pages : 56
Book Description
Acoustic and aerodynamic performance of a 1.5-pressure-ratio, 1.83-meter (6-ft) diameter fan stage for turbofan engines (QF-2)
Author: Richard P. Woodward
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 68
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 68
Book Description
The Gas Turbine Handbook
Author: Tony Giampaolo
Publisher: The Fairmont Press, Inc.
ISBN: 0881734136
Category : Gas-turbines
Languages : en
Pages : 426
Book Description
The second edition of a bestseller, this comprehensive reference provides the fundamental information required to understand both the operation and proper application of all types of gas turbines. The completely updated second edition adds a new section on use of inlet cooling for power augmentation and NOx control. It explores the full spectrum of gas turbines hardware, typical application scenarios, and operating parameters, controls, inlet treatments, inspection, trouble-shooting, and more. The author discusses strategies that can help readers avoid problems before they occur and provides tips that enable diagnosis of problems in their early stages and analysis of failures to prevent their recurrence.
Publisher: The Fairmont Press, Inc.
ISBN: 0881734136
Category : Gas-turbines
Languages : en
Pages : 426
Book Description
The second edition of a bestseller, this comprehensive reference provides the fundamental information required to understand both the operation and proper application of all types of gas turbines. The completely updated second edition adds a new section on use of inlet cooling for power augmentation and NOx control. It explores the full spectrum of gas turbines hardware, typical application scenarios, and operating parameters, controls, inlet treatments, inspection, trouble-shooting, and more. The author discusses strategies that can help readers avoid problems before they occur and provides tips that enable diagnosis of problems in their early stages and analysis of failures to prevent their recurrence.
Scientific and Technical Aerospace Reports
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 296
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 296
Book Description
AGARD Manual on Aeroelasticity in Axial-flow Turbomachines: Unsteady turbomachinery aerodynamics
Author: Max F. Platzer
Publisher:
ISBN: 9789283515432
Category : Aeroelasticity
Languages : en
Pages : 200
Book Description
Publisher:
ISBN: 9789283515432
Category : Aeroelasticity
Languages : en
Pages : 200
Book Description
Encyclopedia of Modern U.S. Military Weapons
Author: Timothy M. Laur
Publisher: Berkley Trade
ISBN: 9780425164372
Category : Military weapons
Languages : en
Pages : 0
Book Description
An accessible encyclopedia of military weapons represents a collaboration with The Army, Navy, and Air Force Times, and covers each weapon system, its evolution, development, and combat experience.
Publisher: Berkley Trade
ISBN: 9780425164372
Category : Military weapons
Languages : en
Pages : 0
Book Description
An accessible encyclopedia of military weapons represents a collaboration with The Army, Navy, and Air Force Times, and covers each weapon system, its evolution, development, and combat experience.