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It outlines how the compressor and integral particle separator interact with engine oil cooling and control electronics airflow, describes the testing and assessment of on-wing icing environments, and summarizes lessons from test and analysis that led to maintenance-resolution changes and associated performance durability impacts. Includes certification test conditions and environmental icing parameters.",{"@graph":69,"@context":122},[70,84,105],{"@type":71,"itemListElement":72},"BreadcrumbList",[73,77,79,82],{"item":74,"name":75,"@type":76,"position":8},"https://docshare.wps.com","Home","ListItem",{"item":78,"name":9,"@type":76,"position":14},"https://docshare.wps.com/document/",{"item":80,"name":40,"@type":76,"position":81},"https://docshare.wps.com/document/research-report/",3,{"item":83,"name":65,"@type":76,"position":19},"https://docshare.wps.com/document/engine-inlet-ice-protection-and-compressor-changes-made-to-resist-ice/651069/",{"url":83,"name":65,"@type":85,"image":86,"author":91,"headline":65,"publisher":94,"fileFormat":97,"inLanguage":63,"description":67,"dateModified":98,"datePublished":99,"encodingFormat":97,"isAccessibleForFree":100,"interactionStatistic":101},"DigitalDocument",{"url":87,"@type":88,"width":89,"height":90},"https://docshare.wps.com/thumbnails/engine-inlet-ice-protection-and-compressor-changes-made-to-resist-ice/651069.png","ImageObject",300,407,{"name":92,"@type":93},"Indoniesian Boy","Person",{"url":74,"name":95,"@type":96},"DocShare","Organization","application/pdf","2026-10-30","2026-10-24",true,{"@type":102,"interactionType":103,"userInteractionCount":19},"InteractionCounter",{"@type":104},"ViewAction",{"@type":106,"mainEntity":107},"FAQPage",[108,114,118],{"name":109,"@type":110,"acceptedAnswer":111},"What problem did General Electric Aircraft Engines begin experiencing in 1984?","Question",{"text":112,"@type":113},"In 1984, General Electric began experiencing an unacceptable level of foreign object damage (FOD) caused by ingested ice in its CT7-5/-7 family of turboprop engines.","Answer",{"name":115,"@type":110,"acceptedAnswer":116},"What were the main goals of the paper?",{"text":117,"@type":113},"The paper addresses stage 1 compressor rotor-blade ice FOD, explains methods for assessing the icing environment, summarizes lessons from test and analysis, and defines the final compressor maintenance resolution that also affected performance deterioration.",{"name":119,"@type":110,"acceptedAnswer":120},"How were icing certification tests described in the document?",{"text":121,"@type":113},"Testing referenced requirements such as FAR 33.67, FAR 25 Appendix C, and Advisory Circular 20-73, with specified icing conditions (e.g., atmospheric temperature, liquid water content, droplet diameter, airspeed, and power settings) and notes on whether engine surfaces remained ice-free and whether ice ingestion occurred.","https://schema.org",{"og:url":83,"og:type":124,"og:title":65,"og:site_name":95,"og:description":67},"article",{"robots":126,"canonical":83},"index,follow",{"doc_id":128,"site_id":62},651069,1792887419,{"code":4,"msg":5,"data":131},{"doc_id":128,"user_id":132,"nickname":92,"user_avatar":133,"doc_module":4,"category_id":39,"category_name":40,"doc_title":65,"doc_description":67,"doc_content":134,"file_id":135,"file_url":136,"file_type":137,"file_size":138,"view_count":19,"is_deleted":4,"is_public":8,"is_downloadable":8,"audit_status":8,"page_count":39,"language":139,"language_code":63,"site_id":62,"html_lang":63,"table_of_contents":140,"faqs":141,"seo_title":142,"seo_description":67,"update_tm":143,"read_time":46},962090760608,"https://ap-avatar.wpscdn.com/davatar_276721f389ce27ea32af1340a28f341c","# ENGINE INLET ICE PROTECTION AND COMPRESSORCHANGES MADE TO RESIST ICE\n\nL.W.Blair,R.L.Miller,D.J.TapparoGeneral Electric Aircraft Engines1000 Western Avenue,Lynn,Massachusetts 01910  \nThe compressor operates behind an integral inertialparticle separator(IPS).The separator system,shown inFigures I-1A and I-1B,is integrated into the power unit oilcooling system and provides airflow to cool the electronicengine control.Originally designed as a sand separator forthe military helicopter environment,the system incorpo-  \n## Introduction\n\nPremise  \nModern high technology turbine aircraft engines oftenemploy high rotor speed compressors with thin advancedblading designs to achieve better performance.The enginedesigner is faced with a tradeoff between optimum com-pressor performance and on-wing durability.During theengine/aircraft development stage,certain assumptions aremade regarding the icing environment and the testingrequired to confirm compatibility with it.Often the trueimpact of the design trade-off is not realized until the en-gine is exposed to its service environment.  \nDespite successful engine test cell and aircraft naturalicing certification tests,in 1984 General Electric AircraftEngines Company began to experience an unacceptablelevel of foreign object damage(FOD)caused by ingestedice with its CT7-5/-7 family of turboprop engines.  \n## Purpose\n\nThe purpose of this paper is:  \nFigure I-1A Engine Inlet Flow Diagram  \n(1)to address the issue of Stage 1 compressor rotorblade ice FOD in the CT7 engine,  \n(2)to explain the methods and techniques used in as-sessing the icing environment,  \n(3)to explain the lessons learned from test and analy-sis,and  \n(4)to define the final resolution of the compressormaintenance problem which simultaneously created accel-erated performance deterioration for the engine.  \nThe paper is divided into two parts,the first dealingwith the airframe icing environment and its impact on theengine inlet system,and the second concentrating on thedesign improvement and durability testing of the Stage 1compressor blade.  \nFigure I-1B Inlet Frame,Mainframe,IGV Casing Assembly  \nPARTI  \nrated swirl and deswirl vanes to optimize efficiency.It hassince been changed from a swirl concept to a straight axialbypass to reduce pressure loss and improve performance.  \n## Basic Engine Design\n\nThe CT7 turboprop engine is a free-turbine modulardesign derivative of the T700 turboshaft engine.It employs  \na five-stage variable stator axial and single stage centrifugal Inlet and Installed Icing Environmentcompressor with a combined pressure ratio of 18:1.The airframe-provided inlet design is a conventionalS-duct with a throat area optimized to aircraft specifica-tions.An inlet protection device(IPD)is incorporated tomeet bird ingestion certification requirements.  \nResponsibility for inlet aerodynamics was assumed bythe engine manufacturer.The airframer assumed responsi-bility for the mechanical design,structural integrity,anti-icing,test and procurement.  \n\n| (REF    | AC 20-73   | )   |  |\n| --- | --- | --- | --- |\n| ENVIRONMENTALICING TEST CONDITIONS   |  |  |  |\n| Condition Number   | 1   | 2   | 3   |\n| Atmospheric Temperature,°F   | 29   | 23   | -4   |\n| Liquid Water Content  \u003Cbr>minimum).grammeter3   | 0.3   | 2.0   | 1.0   |\n| Mean Eflective Drop Diameter,microns   |  40   | 25   | 15   |\n| Icing Condition Power Settings   | Ground Idle   | Flight ldle  \u003Cbr>50%Max Cont   \u003Cbr>75%Max Cont   \u003Cbr>Takeoff   | Flight ldle  \u003Cbr>50%Max Cont  \u003Cbr>75%Max Cont  \u003Cbr>Takeoff   |\n| Duration at each of the power  \u003Cbr>setings specilled above,(minutes)   | 30   | 10   | 10   |\n\nOther areas forward of the engine,which are subject tothe icing environment are shown in Figure I-2.Propellerspinners on both applications are parabolic profile andunheated (neither anti-iced nor de-iced).Original ice-shedtrajectory analyses showed no ingestion into either inletdesign.Later analytical refinements reversed this findingfor accumulations on the","cbCaiiZkbKu7zEoY","https://ap.wps.com/l/cbCaiiZkbKu7zEoY","pdf",2013467,"English","# Introduction\n## Premise\n## Purpose\n# Basic Engine Design\n# ENGINE ICING CERTIFICATION TEST CONDITIONS\n## Inlet and installation environment testing","[{\"question\":\"What problem did General Electric Aircraft Engines begin experiencing in 1984?\",\"answer\":\"In 1984, General Electric began experiencing an unacceptable level of foreign object damage (FOD) caused by ingested ice in its CT7-5/-7 family of turboprop engines.\"},{\"question\":\"What were the main goals of the paper?\",\"answer\":\"The paper addresses stage 1 compressor rotor-blade ice FOD, explains methods for assessing the icing environment, summarizes lessons from test and analysis, and defines the final compressor maintenance resolution that also affected performance deterioration.\"},{\"question\":\"How were icing certification tests described in the document?\",\"answer\":\"Testing referenced requirements such as FAR 33.67, FAR 25 Appendix C, and Advisory Circular 20-73, with specified icing conditions (e.g., atmospheric temperature, liquid water content, droplet diameter, airspeed, and power settings) and notes on whether engine surfaces remained ice-free and whether ice ingestion occurred.\"}]","ENGINE INLET ICE PROTECTION AND COMPRESSOR CHANGES MADE TO RESIST ICE | PDF",1792859056]