1、_ SAE Technical Standards Board Rules provide that: “This report is published by SAE to advance the state of technical and engineering sciences. The use of this report is entirely voluntary, and its applicability and suitability for any particular use, including any patent infringement arising there
2、from, is the sole responsibility of the user.” SAE reviews each technical report at least every five years at which time it may be revised, reaffirmed, stabilized, or cancelled. SAE invites your written comments and suggestions. Copyright 2017 SAE International All rights reserved. No part of this p
3、ublication may be reproduced, stored in a retrieval system or transmitted, in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without the prior written permission of SAE. TO PLACE A DOCUMENT ORDER: Tel: 877-606-7323 (inside USA and Canada) Tel: +1 724-776-497
4、0 (outside USA) Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.org SAE values your input. To provide feedback on this Technical Report, please visit http:/standards.sae.org/AIR6189 AEROSPACE INFORMATION REPORT AIR6189 Issued 2017-09 Design, Calibration, and Test Metho
5、ds for Turbine Engine Icing Test Facilities RATIONALE The aim of the document is to assemble and record the current knowledge and test processes for the use of the engine icing test facilities in support of airworthiness certification. There is a particular need to identify and understand the define
6、d test processes that have the greatest influence on the accuracy of the results. The document will address the key concerns and illustrate some of the different types of approached used. TABLE OF CONTENTS 1. SCOPE 4 1.1 Background . 4 1.2 Purpose . 4 2. REFERENCES 4 2.1 Applicable Documents 4 2.1.1
7、 SAE Publications . 4 2.1.2 FAA Publications . 5 2.1.3 NASA Scientific and Technical Information Program 5 2.1.4 U.S. Government Publications 5 2.1.5 U.S. Military Technical Reports . 5 2.2 Definitions 5 2.3 Abbreviations . 7 3. CLARIFICATION OF TERMS . 8 4. REGULATORY ICING ENVELOPES AND REQUIREMEN
8、TS . 8 4.1 Regulatory Icing Envelopes . 8 4.1.1 In-Flight Icing . 8 4.1.2 Icing Environments 8 4.1.3 Test Requirements for Simulated In-Flight Icing Conditions . 9 4.1.4 Application to Engine Test Operating Conditions 9 4.1.5 Ground Operations Icing Conditions . 9 5. COMMENTS ON USE OF REGULATIONS 9
9、 5.1 Icing Facility Cloud Characteristics . 9 5.2 Conducting an Icing Test 10 5.3 Facility Requirements 10 5.3.1 Minimum Facility Capabilities to Meet Regulatory Test Requirements . 10 5.3.2 Anti-Ice for the Inlet System 11 SAE INTERNATIONAL AIR6189 Page 2 of 56 6. FACILITIES DESCRIPTION . 11 6.1 Fr
10、eejet . 11 6.1.1 General Description of Functional Capabilities and Performance Range . 11 6.1.2 Design Considerations 12 6.1.3 Advantages and Limitations of Configuration 12 6.2 Direct Connect. 13 6.2.1 General Description of Functional Capabilities and Performance Range . 13 6.2.2 Advantages and L
11、imitations of Configuration 16 6.3 Bypass . 17 6.3.1 General Description of Functional Capabilities and Performance Range . 17 6.3.2 Advantages and Limitations of the Bypass Configuration . 17 6.4 Additional Facility Requirements . 18 6.4.1 Steady State and Rapid Power Changes and the Ability to Del
12、iver Conditioned Air . 18 6.4.2 Humidity Control 18 6.4.3 Turboshaft/Turboprop Engine Test Considerations 18 7. SIMULATED ICING CLOUD GENERATION 19 7.1 Spray Systems 19 7.1.1 Nozzle Array Spacing 19 7.1.2 Nozzle Water Supply Systems 20 7.1.3 Nozzle Air Supply Systems . 22 7.2 Spray Nozzles . 23 7.2.
13、1 Internal Mixed Nozzles versus External Mixed Nozzles 23 7.2.2 Droplet Size Distribution 23 7.2.3 Factors that Affect MVD, MEDD . 23 8. CLOUD MEASUREMENT METHODS 24 8.1 Liquid Water Content (LWC) . 24 8.1.1 SEA LWC-1000 (JW) and LWC-2000 (Multi-Wire) System 24 8.1.2 SEA Robust Probe 25 8.1.3 Nevzor
14、ov Probe . 25 8.1.4 King Probe . 25 8.1.5 UTC Aerospace Systems (Rosemount) Vibrating Cylinder Ice Detector (RICE) 26 8.2 Droplet Size Measurement Methods . 26 8.2.1 Other Droplet Sizing Methods . 27 8.3 Icing Cloud Uniformity . 27 8.3.1 Icing Cloud Extent (i.e., Diameter of Cloud) 29 9. ENVIRONMENT
15、 MEASUREMENTS 29 9.1 Humidity 29 9.1.1 Measurement Methods and Operational Considerations 29 9.2 Static/Total Air Temperature . 30 9.2.1 Measurement Methods and Operational Considerations 30 9.3 Icing Cloud Airflow Velocity . 30 9.4 Droplet Temperature . 31 9.4.1 Unintentional Freeze Out (i.e., Mixe
16、d Phase) . 32 9.5 Instrumentation (Measurements for Engine Testing) 32 9.5.1 Measurement Techniques . 32 9.5.2 Instrumentation Equipment . 32 9.5.3 Measurement Uncertainty . 33 10. ICING CLOUD CALIBRATION 33 10.1 Nozzles 33 10.1.1 Frequency of Calibration . 33 10.1.2 Calibration Procedures 33 10.2 S
17、pray Array 33 10.2.1 Overview of Process . 33 10.3 Freejet Cloud Calibration . 34 10.3.1 Calibration Procedures 35 10.4 Operational Restrictions, Limitations, and Out-of-Tolerance Conditions 36 SAE INTERNATIONAL AIR6189 Page 3 of 56 11. NOTES 36 11.1 Revision Indicator 36 APPENDIX A DELEGATION GENER
18、ALE POUR LARMEMENT (DGA) AERO ENGINES . 37 APPENDIX B GLOBAL AEROSPACE CENTRE FOR ICING AND ENVIRONMENTAL RESEARCH, INC. (GLACIER) 41 APPENDIX C GENERAL ELECTRIC AVIATION WINNIPEG AND PEEBLES . 46 APPENDIX D NATIONAL AERONAUTICS AND SPACE ADMINISTRATION PROPULSION SYSTEMS LABORATORY (PSL) . 47 APPEN
19、DIX E NATIONAL RESEARCH COUNCIL CANADA (NRC) GAS TURBINE LABORATORY (GTL) . 51 APPENDIX F UNITED STATES AIR FORCE ARNOLD ENGINEERING DEVELOPMENT CENTER (AEDC) . 53 APPENDIX G UNITED STATES AIR FORCE MCKINLEY CLIMATIC LABORATORY 56 Figure 1 Freejet Facility . 11 Figure 2 Schematic of Freejet Facility
20、 . 12 Figure 3 Typical setup for an engine driven direct connect system 14 Figure 4 Slip joint section and viewing area 16 Figure 5 Bypass configuration . 17 Figure 6 Schematic for icing cloud spray rig . 19 Figure 7 Schematic for icing cloud spray rig (top view) . 20 Figure 8 Icing cloud spray rig
21、system schematic (water pressure control system) . 21 Figure 9 Icing cloud spray rig control system schematic (water flow control system) . 21 Figure 10 SEA icing probes . 25 Figure 11 Freejet test cell showing grid uniformity 28 Figure 12 Freejet test cell grid close-up 29 Figure 13 Example of a hy
22、draulic map used during calibration of test facility . 35 Table 1 Langmuir distributions . 6 SAE INTERNATIONAL AIR6189 Page 4 of 56 1. SCOPE This SAE Aerospace Information Report (AIR) provides descriptions of test procedures and established practices for the application, use, and administration of
23、the conduct of icing testing for all types of turbine engines in conventional supercooled liquid (14 CFR Part 25 Appendix C) environmental conditions in ground test facilities (sea-level and altitude) for icing certification purposes. 1.1 Background The U.S. Federal Aviation Administration has reque
24、sted that SAE International establish current practices and guidelines for the acceptable use of engine icing test facilities and test methods to support certification. SAE has already developed a series of Aerospace Recommended Practices (ARP) documents for other icing certification engineering too
25、ls. These documents: ARP5903, Droplet Impingement and Ice Accretion Computer Codes, ARP5904, Airborne Icing Tankers, and ARP5905, Calibration and Acceptance of Icing Wind Tunnels were developed to address the calibration and procedures used for icing computer codes, icing tankers, and icing wind tun
26、nels respectively. ARP5905 states that it is not applicable to engine icing test facilities. There was a need to begin the process of identifying the issues associated with engine icing facilities. At this time the industry consensus was that the current facilities and their historical test experien
27、ces can be significantly different and there are not a set of common test practices across their use. The SAE committees involved in the development of this document determined that an ARP is not appropriate at this time, so the intention is to create an Aerospace Information Report (AIR) first to i
28、dentify the methods and equipment currently used. 1.2 Purpose The purpose of this AIR is to compile, in one definitive source, the currently utilized mature methods and procedures for calibration and acceptance criteria for turbine engine icing test facilities. Facilities that meet these criteria wi
29、ll have icing conditions simulation capability. The scope covers both sea-level and altitude engine icing facilities. 2. REFERENCES 2.1 Applicable Documents The following publications form a part of this document to the extent specified herein. The latest issue of SAE publications shall apply. The a
30、pplicable issue of other publications shall be the issue in effect on the date of the purchase order. In the event of conflict between the text of this document and references cited herein, the text of this document takes precedence. Nothing in this document, however, supersedes applicable laws and
31、regulations unless a specific exemption has been obtained.SAE Publications 2.1.1 SAE Publications Available from SAE International, 400 Commonwealth Drive, Warrendale, PA 15096-0001, Tel: 877-606-7323 (inside USA and Canada) or +1 724-776-4970 (outside USA), www.sae.org. AIR4906 Droplet Sizing Instr
32、umentation Used in Icing Facilities AIR5026A Test Cell Instrumentation ARP5305 Structural Design and Construction Considerations for Enclosed Turbofan/Turbojet Engine Test Cells ARP5624 Aircraft Inflight Icing Terminology ARP5904 Airborne Icing Tankers ARP5905 Calibration and Acceptance of Icing Win
33、d Tunnels SAE INTERNATIONAL AIR6189 Page 5 of 56 2.1.2 FAA Publications Available from Federal Aviation Administration, 800 Independence Avenue, SW, Washington, DC 20591, Tel: 866-835-5322, www.faa.gov. Title 14 of the Code of Federal Regulations (14 CFR), Part 25 and Part 33, Federal Aviation Admin
34、istration FAA Advisory Circular 20-147A, “Turbojet, Turboprop, Turboshaft, and Turbofan Engine Induction System Icing and Ice Ingestion” 2.1.3 NASA Scientific and Technical Information Program Copies of these documents are available at https:/www.sti.nasa.gov/. NASA Technical Memorandum TM-102447, “
35、Liquid Water Content and Droplet Size Calibration of the NASA Lewis Icing Research Tunnel,” Ide, R., January 1990 NASA Technical Memorandum TM-2008-215177, “2006 Icing Cloud Calibration of the NASA Glenn Icing Research Tunnel,” Ide, R. and Sheldon, D., May 2008 2.1.4 U.S. Government Publications Cop
36、ies of these documents are available at https:/ntrl.ntis.gov/NTRL. DOT/FAA/AR-TN06 “Cloud Sampling Instruments for Icing Flight Tests,” Jeck, R., 2006 DOT/FAA/AR-07/4, “Advances in the Characterization of Supercooled Clouds for Aircraft Icing Applications”, November 2008, Jeck, R., Federal Aviation
37、Administration 2.1.5 U.S. Military Technical Reports Copies of these documents are available at http:/www.dtic.mil/dtic. AEDC Evaporation model paper: “A Kinetic Model for Two-Phase Flow in High Temperature Exhaust Gas Coolers,” Pelton and Willbanks, AEDC-TR-72-89, 1972 2.2 Definitions The following
38、 terms are used in this document. The SAE Aircraft Inflight Icing Terminology (ARP5624) is a resource for the definition of additional icing terms. AMBIENT TEMPERATURE: Ambient temperature is representative of the static temperature at flight ambient condition. This is true for a capture ratio of 1.
39、 “APPENDIX C”: The current FAA engineering standard for atmospheric icing, Title 14 of the Code of Federal Regulations (14 CFR), Part 25. Appendix C consists of two envelopes, the continuous maximum and the intermittent maximum, defined by liquid water content, droplet size, static air temperature,
40、and horizontal extent. These curves can be found at the Government Printing Offices website, or at the following link http:/www.gpo.gov/fdsys/pkg/CFR-2011-title14-vol1/pdf/CFR-2011-title14-vol1-part25-appC.pdf. “APPENDIX D”: A new engineering standard identified for high altitude convective weather
41、ice crystal icing conditions, found in 14 CFR Part 33. “APPENDIX O”: A new engineering standard identified for large droplet icing conditions where the drops exceed the current Appendix C engineering standards. The curves describing these icing conditions can be found in 14 CFR Part 25. GROUND FOG:
42、Fog is a surface based cloud composed of either water droplets or ice crystals. It is created when radiational cooling at the earths surface lowers the temperature of the air near the ground to or below its initial dew point. Primarily takes place at night or early morning. SAE INTERNATIONAL AIR6189
43、 Page 6 of 56 DEW POINT TEMPERATURE: The temperature to which a given air parcel must be cooled at constant pressure and constant water vapor content in order to achieve saturation with respect to water. (ARP5624) DROPLET: A small spherical particle of any liquid; in meteorology, particularly a wate
44、r drop. There is no defined size limit separating drops from droplets of water, but it is sometimes convenient to denote two disparate size ranges, such as the oft-used distinction of liquid cloud particles (droplets) from liquid precipitation (drops), thereby implying that a maximum diameter of 0.2
45、 mm is the limit for droplets. (ARP5624) LANGMUIR DISTRIBUTION: A family of five hypothetical, symmetrical LWC vs. droplet size distributions originally devised for analyzing ROTATING MULTICYLINDER (RMC) measurements. The table gives the droplet diameter as a fraction or multiple of the MEDIAN VOLUM
46、ETRIC DIAMETER (MVD) for the center of each of the seven LWC intervals in each column. The table illustrates the distributions in terms of a/a0, where a is the average diameter in each group and a0 is the median volumetric diameter. Distribution “D” or “E” are commonly used for ice accretion computa
47、tions on airfoils as assumed in 14 CFR-25,29 Appendix C. (ARP5624) Appendix C assumes Distributon “A” which is suitable for accretion, but Distribution “D” or “E” should be used for droplet impingement limits or the calculation of ice limits. Table 1 - Langmuir distributions a/a0 %LWC A B C D E 5% 1
48、.00 0.56 0.42 0.31 0.23 10% 1.00 0.72 0.61 0.52 0.44 20% 1.00 0.84 0.77 0.71 0.65 30% 1.00 1.00 1.00 1.00 1.00 20% 1.00 1.17 1.26 1.37 1.48 10% 1.00 1.32 1.51 1.74 2.00 5% 1.00 1.49 1.81 2.22 2.71 LIQUID WATER CONTENT (LWC): The mass of water contained in liquid cloud droplets within a unit volume,
49、usually given in units of grams of water per cubic meter of air (g/m3). MEAN ARITHMETIC DIAMETER (MAD): A droplet diameter used by the Aviation Register of Russia (MAK). MEDIAN VOLUMETRIC DIAMETER (MVD) Also referred to as Median Volume Diameter: The droplet diameter, usually given in micrometers (10-6 m), such that one-half the liquid water volume is contained in droplets smaller than the median volume diameter and one-half the liquid wa
