scholarly journals Preliminary Results from a Heavily Instrumented Engine Ice Crystal Icing Test in a Ground Based Altitude Test Facility

2016 ◽  
Author(s):  
Ashlie B. Flegel ◽  
Michael J. Oliver
Keyword(s):  
Test Facility ◽  
Ice Crystal ◽  
Preliminary Results

Evaluation of a 12-Hour/Day Shift Schedule

1986 ◽  
Vol 30 (9) ◽  
pp. 885-889 ◽  
Author(s):  
Paul M. Lewis ◽  
Dan J. Swaim
Keyword(s):  
Job Satisfaction ◽  
Plant Performance ◽  
Test Facility ◽  
Work Schedule ◽  
Sleep Health ◽  
Evaluation Program ◽  
Preliminary Results ◽  
Shift Schedule ◽  
Reasonable Alternative ◽  
Fast Flux

In April 1985, the operating crews at the Fast Flux Test Facility near Richland, Washington, changed their rotating shift schedule from an 8- to a 12-hour/day work schedule. The primary purpose of the change was to reduce the attrition of operators by increasing their job satisfaction. Eighty-four percent of the operators favored the change. A program was established to evaluate the effects on plant performance, operator alertness, attrition, sleep, health, job satisfaction, and off- the-job satisfaction. Preliminary results from that evaluation program indicate that the 12-hour shift schedule is a reasonable alternative to an 8-hour schedule at this facility.

Analysis of the Honeywell Uncertified Research Engine With Ice Crystal Cloud Ingestion at Simulated Altitudes

2020 ◽  
Vol 142 (6) ◽  
Author(s):  
Philip C. E. Jorgenson ◽  
Joseph P. Veres ◽  
Samaun Nili ◽  
Shashwath R. Bommireddy ◽  
Kenneth L. Suder
Keyword(s):  
Operating Conditions ◽  
Test Facility ◽  
Inlet Guide Vane ◽  
Transfer Model ◽  
Ice Accretion ◽  
Ice Crystal ◽  
Turbofan Engine ◽  
Test Matrix ◽  
Compression System ◽  
Ice Cloud

Abstract The Honeywell Uncertified Research Engine (HURE), a research version of a turbofan engine that never entered production, was tested in the NASA Propulsion Systems Laboratory (PSL), an altitude test facility at the NASA Glenn Research Center. The PSL is a facility that is equipped with water spray bars capable of producing an ice cloud consisting of ice particles, having a controlled particle diameter and concentration in the airflow. To develop the test matrix of the HURE, the numerical asw analysis of flow and ice particle thermodynamics was performed on the compression system of the turbofan engine to predict operating conditions that could potentially result in a risk of ice accretion due to ice crystal ingestion. The goal of the test matrix was to provide operating conditions such that ice would accrete either in the fan-stator through the inlet guide vane region of the compression system or within the first stator of the high-pressure compressor. The predictive analyses were performed with the mean-line compressor flow modeling code (comdes-melt) which includes an ice particle model. The HURE engine was tested in PSL with the ice cloud over the range of operating conditions of altitude, ambient temperature, simulated flight Mach number, and fan speed with guidance from the analytical predictions. The engine was fitted with video cameras at strategic locations within the engine compression system flow path where ice was predicted to accrete in order to visually confirm ice accretion when it occurred. In addition, traditional compressor instrumentation, such as total pressure and temperature probes, static pressure taps, and metal temperature thermocouples, were installed in targeted areas where the risk of ice accretion was expected. The current research focuses on the analysis of the data that were obtained after testing the HURE engine in PSL with ice crystal ingestion. The computational method (comdes-melt) was enhanced by computing key parameters through the fan-stator at multiple spanwise locations in order to increase the fidelity with the current mean-line method. The Icing Wedge static wet-bulb temperature thresholds were applied for determining the risk of ice accretion in the fan-stator, which is thought to be an adiabatic region. At some operating conditions near the splitter–lip region, other sources of heat (non-adiabatic walls) were suspected to be the cause of accretion, and the Icing Wedge was not applied to predict accretion at that location. A simple order-of-magnitude heat transfer model was implemented into the comdes-melt code to estimate the wall temperature minimum and maximum thresholds that support ice accretion, as observed by video confirmation. The results from this model spanned the range of wall temperatures measured on a previous engine that experienced ice accretion at certain operating conditions. The goal of this study is to show that the computational process developed on earlier engine icing tests can be used to provide an icing risk assessment in adiabatic regions for other engines.

scholarly journals Analysis of the Honeywell Uncertified Research Engine (HURE) With Ice Crystal Cloud Ingestion at Simulated Altitudes

2019 ◽  
Author(s):  
Joseph P. Veres ◽  
Philip C. E. Jorgenson ◽  
Samaun Nili ◽  
Shashwath R. Bommireddy ◽  
Kenneth L. Suder
Keyword(s):  
Operating Conditions ◽  
Test Facility ◽  
Inlet Guide Vane ◽  
Transfer Model ◽  
Ice Accretion ◽  
Ice Crystal ◽  
Turbofan Engine ◽  
Test Matrix ◽  
Compression System ◽  
Ice Cloud

Abstract The Honeywell Uncertified Research Engine (HURE), a research version of a turbofan engine that never entered production, was tested in the NASA Propulsion System Laboratory (PSL), an altitude test facility at the NASA Glenn Research Center. The PSL is a facility that is equipped with water spray bars capable of producing an ice cloud consisting of ice particles, having a controlled particle diameter and concentration in the air flow. To develop the test matrix of the HURE, numerical analysis of flow and ice particle thermodynamics was performed on the compression system of the turbofan engine to predict operating conditions that could potentially result in a risk of ice accretion due to ice crystal ingestion. The goal of the test matrix was to provide operating conditions such that ice would accrete in either the fan-stator through the inlet guide vane region of the compression system or within the first stator of the high pressure compressor. The predictive analyses were performed with the mean line compressor flow modeling code (COMDES-MELT) which includes an ice particle model. The HURE engine was tested in PSL with the ice cloud over the range of operating conditions of altitude, ambient temperature, simulated flight Mach number, and fan speed with guidance from the analytical predictions. The engine was fitted with video cameras at strategic locations within the engine compression system flow path where ice was predicted to accrete, in order to visually confirm ice accretion when it occurred. In addition, traditional compressor instrumentation such as total pressure and temperature probes, static pressure taps, and metal temperature thermocouples were installed in targeted areas where the risk of ice accretion was expected. The current research focuses on the analysis of the data that was obtained after testing the HURE engine in PSL with ice crystal ingestion. The computational method (COMDES-MELT) was enhanced by computing key parameters through the fan-stator at multiple span wise locations, in order to increase the fidelity with the current mean-line method. The Icing Wedge static wet bulb temperature thresholds were applicable for determining the risk of ice accretion in the fan-stator, which is thought to be an adiabatic region. At some operating conditions near the splitter-lip region, other sources of heat (non-adiabatic walls) were suspected to be the cause of accretion, and the Icing Wedge was not applicable to predict accretion at that location. A simple order-of-magnitude heat transfer model was implemented into the COMDES-MELT code to estimate the wall temperature minimum and maximum thresholds that support ice accretion, as observed by video confirmation. The results from this model spanned the range of wall temperatures measured on a previous engine that experienced ice accretion at certain operating conditions. The goal of this study is to show that the computational process developed on earlier engine icing tests can be used to provide an icing risk assessment in adiabatic regions for other engines.

scholarly journals River-ice Fabrics: Preliminary Results

1971 ◽  
Vol 10 (58) ◽  
pp. 151-152
Author(s):  
N.P. Lasca
Keyword(s):  
Preliminary Data ◽  
Stream Flow ◽  
River Ice ◽  
Ice Crystal ◽  
Preliminary Results ◽  
Ice Surface ◽  
Crystal Orientations ◽  
Response To Stress ◽  
Ice Fabrics

AbstractPreliminary data indicate that fabric is developed in river ice. Crystal orientations are usually sub-parallel to the ice surface, and develop partly in response to stress generated by stream flow.

Boundary Conditions for Compressor Cascade Ice Crystal Icing Testing

2020 ◽  
Author(s):  
Matthias Nagorski ◽  
Christian Koch ◽  
Stephan Staudacher
Keyword(s):  
Target Surface ◽  
Test Facility ◽  
Ice Crystal ◽  
Compressor Cascade ◽  
Power Setting ◽  
Ice Water Content ◽  
Linear Compressor Cascade ◽  
The University ◽  
Ice Water ◽  
Operating Points

Abstract At the Altitude Test Facility (ATF) of the University of Stuttgart a linear compressor cascade test rig serves the investigation of ice crystal icing (ICI) under engine realistic conditions. A numerical model of the first stage of NASA Stage 67 is validated with experimental data taken from literature and used to investigate the respective ice crystal icing conditions for prospective cascade experiments. Eleven operating points simulating climb conditions with constant non-dimensional power setting through ascending parcels of moist air are selected for analysis. Only the melting-dominated regime is considered. The 3D flow field is obtained using a RANS approach in combination with a Spalart-Allmaras one-equation turbulence model. The droplet and ice crystal trajectories are calculated based on an Eulerian framework. The computation of the surface energy balance is adapted from the Messinger model taking into account unsteady phenomena. Four of eleven selected operating points indicate the onset of substantial ice accretion. A static wet bulb temperature of freezing constitutes in general the lower icing limit for rig experiments. The upper icing limit depends on the ice water content impinging and sticking to the target surface.

Boundary Conditions for Compressor Cascade Ice Crystal Icing Testing

2021 ◽  
pp. 1-16
Author(s):  
Matthias Nagorski ◽  
Christian Koch ◽  
Stephan Staudacher
Keyword(s):  
Target Surface ◽  
Test Facility ◽  
Ice Crystal ◽  
Compressor Cascade ◽  
Power Setting ◽  
Ice Water Content ◽  
Linear Compressor Cascade ◽  
The University ◽  
Ice Water ◽  
Operating Points

Abstract At the Altitude Test Facility (ATF) of the University of Stuttgart a linear compressor cascade test rig serves the investigation of ice crystal icing (ICI) under engine realistic conditions. A numerical model of the first stage of NASA Stage 67 is validated with experimental data taken from literature and used to investigate the respective ice crystal icing conditions for prospective cascade experiments. Eleven operating points simulating climb conditions with constant non-dimensional power setting through ascending parcels of moist air are selected for analysis. Only the melting-dominated regime is considered. The 3D flow field is obtained using a RANS approach in combination with a Spalart-Allmaras one-equation turbulence model. The droplet and ice crystal trajectories are calculated based on an Eulerian framework. The computation of the surface energy balance is adapted from the Messinger model taking into account unsteady phenomena. Four of eleven selected operating points indicate the onset of substantial ice accretion. A static wet bulb temperature of freezing constitutes in general the lower icing limit for rig experiments. The upper icing limit depends on the ice water content impinging and sticking to the target surface.

scholarly journals Preparation for Scaling Studies of Ice-Crystal Icing at the NRC Research Altitude Test Facility

2013 ◽  
Author(s):  
Peter M. Struk ◽  
Timothy Bencic ◽  
Jen-Ching Tsao ◽  
Dan Fuleki ◽  
Daniel C. Knezevici
Keyword(s):  
Test Facility ◽  
Ice Crystal
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