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Analytical Study of Icing Simulation for Turbine Engines in Altitude Test Cells.

AD770069

Publication Date	1973
Personal Author	Willbanks, C. E.; Schulz, R. J.
Page Count	98
Abstract	An analytical study of simulated icing for turbine engines in altitude test cells was made. A mathematical model of a typical direct-connect type of icing test cell was developed and the governing equations were programmed for computer solution on FORTRAN computer language. A parametric study was performed to determine the effects of the test cell inlet and water spray conditions on the thermodynamic and kinetic state of the flow in the test section or at the engine compressor face. The importance of correctly simulating droplet size distribution, mean effective droplet diameter, liquid water content, and humidity was investigated. The results of the investigation lend further support to the fact that ground test facilities provide the best capability for conducting turbine engine icing tests. The ability to define and control the simulated environment gives an altitude test cell distinct advantages not enjoyed by flight testing in natural icing environments or flight testing in artificial environments created by tanker aircraft. (Author)
Keywords	Jet engines Ice formation Ice Particles Test facilities Simulation Meteorological data Temperature Test methods Test cells
Source Agency	Invalid Source Agency Code
NTIS Subject Category	81D - Jet & Gas Turbine Engines
Corporate Authors	Arnold Engineering Development Center Arnold Air Force Station Tenn
Supplemental Notes	Prepared in cooperation with ARO, Inc., Tullahoma, Tenn. Rept. no. ARO-ETF-TR-73-59.
Document Type	Technical Report
Title Note	Final rept. Jun 71-Jun 72.
NTIS Issue Number	197402

Analytical Study of Icing Simulation for Turbine Engines in Altitude Test Cells.

Analytical Study of Icing Simulation for Turbine Engines in Altitude Test Cells.
AD770069

Publication Date	1973
Personal Author	Willbanks, C. E.; Schulz, R. J.
Page Count	98
Abstract	An analytical study of simulated icing for turbine engines in altitude test cells was made. A mathematical model of a typical direct-connect type of icing test cell was developed and the governing equations were programmed for computer solution on FORTRAN computer language. A parametric study was performed to determine the effects of the test cell inlet and water spray conditions on the thermodynamic and kinetic state of the flow in the test section or at the engine compressor face. The importance of correctly simulating droplet size distribution, mean effective droplet diameter, liquid water content, and humidity was investigated. The results of the investigation lend further support to the fact that ground test facilities provide the best capability for conducting turbine engine icing tests. The ability to define and control the simulated environment gives an altitude test cell distinct advantages not enjoyed by flight testing in natural icing environments or flight testing in artificial environments created by tanker aircraft. (Author)
Keywords	Jet engines Ice formation Ice Particles Test facilities Simulation Meteorological data Temperature Test methods Test cells
Source Agency	Invalid Source Agency Code
NTIS Subject Category	81D - Jet & Gas Turbine Engines
Corporate Authors	Arnold Engineering Development Center Arnold Air Force Station Tenn
Supplemental Notes	Prepared in cooperation with ARO, Inc., Tullahoma, Tenn. Rept. no. ARO-ETF-TR-73-59.
Document Type	Technical Report
Title Note	Final rept. Jun 71-Jun 72.
NTIS Issue Number	197402