scholarly journals Possible Mechanisms for Turbofan Engine Ice Crystal Icing at High Altitude

2014 ◽  
Author(s):  
Jen-Ching Tsao ◽  
Peter M. Struk ◽  
Michael J. Oliver
Keyword(s):  
High Altitude ◽  
Ice Crystal ◽  
Turbofan Engine

scholarly journals Optimization for the Starting Process of Turbofan Engine Under High-Altitude Environment

IEEE Access ◽  
2018 ◽  
Vol 6 ◽  
pp. 55797-55806
Author(s):  
Ma Song ◽  
Tan Jianguo ◽  
Su Sanmai ◽  
Zhu Mingyan
Keyword(s):  
High Altitude ◽  
Turbofan Engine ◽  
Starting Process

scholarly journals Tropical deep convective life cycle: Cb-anvil cloud microphysics from high-altitude aircraft observations

2014 ◽  
Vol 14 (23) ◽  
pp. 13223-13240 ◽  
Author(s):  
W. Frey ◽  
S. Borrmann ◽  
F. Fierli ◽  
R. Weigel ◽  
V. Mitev ◽  
...  
Keyword(s):  
Life Cycle ◽  
High Altitude ◽  
Potential Temperature ◽  
Cloud Microphysics ◽  
Mature Stage ◽  
Convective System ◽  
Ice Crystal ◽  
Convective Clouds ◽  
Tropical Tropopause ◽  
Deep Convective Clouds

Abstract. The case study presented here focuses on the life cycle of clouds in the anvil region of a tropical deep convective system. During the SCOUT-O3 campaign from Darwin, Northern Australia, the Hector storm system has been probed by the Geophysica high-altitude aircraft. Clouds were observed by in situ particle probes, a backscatter sonde, and a miniature lidar. Additionally, aerosol number concentrations have been measured. On 30 November 2005 a double flight took place and Hector was probed throughout its life cycle in its developing, mature, and dissipating stage. The two flights were four hours apart and focused on the anvil region of Hector in altitudes between 10.5 and 18.8 km (i.e. above 350 K potential temperature). Trajectory calculations, satellite imagery, and ozone measurements have been used to ensure that the same cloud air masses have been probed in both flights. The size distributions derived from the measurements show a change not only with increasing altitude but also with the evolution of Hector. Clearly different cloud to aerosol particle ratios as well as varying ice crystal morphology have been found for the different development stages of Hector, indicating different freezing mechanisms. The development phase exhibits the smallest ice particles (up to 300 μm) with a rather uniform morphology. This is indicative for rapid glaciation during Hector's development. Sizes of ice crystals are largest in the mature stage (larger than 1.6 mm) and even exceed those of some continental tropical deep convective clouds, also in their number concentrations. The backscatter properties and particle images show a change in ice crystal shape from the developing phase to rimed and aggregated particles in the mature and dissipating stages; the specific shape of particles in the developing phase cannot be distinguished from the measurements. Although optically thin, the clouds in the dissipating stage have a large vertical extent (roughly 6 km) and persist for at least 6 h. Thus, the anvils of these high-reaching deep convective clouds have a high potential for affecting the tropical tropopause layer by modifying the humidity and radiative budget, as well as for providing favourable conditions for subvisible cirrus formation. The involved processes may also influence the amount of water vapour that ultimately reaches the stratosphere in the tropics.

Total air temperature anomalies as a metric for detecting high-altitude ice crystal events: Development of a failure indicator heuristic

2019 ◽  
Vol 105 ◽  
pp. 982-1005
Author(s):  
Álvaro Rodríguez-Sanz ◽  
Rosa Arnaldo Valdés ◽  
Fernando Gómez Comendador ◽  
Eduardo Sánchez Ayra ◽  
Javier Cano Cancela
Keyword(s):  
High Altitude ◽  
Air Temperature ◽  
Ice Crystal ◽  
Temperature Anomalies ◽  
Air Temperature Anomalies

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.

Ice Crystal Ingestion in a Turbofan Engine

2015 ◽  
Author(s):  
Matthew Feulner ◽  
Shengfang Liao ◽  
Becky Rose ◽  
Xuejun Liu
Keyword(s):  
Ice Crystal ◽  
Turbofan Engine

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.

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