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- W1517504868 abstract "Abstract A fundamental analysis of the matching of the rotating components of a gas turbine engine and their integration into an airframe is presented. Similarity variables are introduced to characterize the operation of the rotating engine components. Performance maps of compressors and turbines are used to illustrate the manner in which they may be matched in terms of power, mass flow, and shaft speed. Because one engine may be used in several different aircraft it must be properly integrated in each. The specific case of matching inlet performance and engine airflow requirements is discussed. An analysis of thrust generation in an aircraft is performed to identify those parameters necessary for monitoring and controlling the thrust in flight. An illustration of the importance of proper positioning of the terminal shock in supersonic inlets and means for controlling that position is presented." @default.
- W1517504868 created "2016-06-24" @default.
- W1517504868 creator A5074583556 @default.
- W1517504868 date "2012-12-17" @default.
- W1517504868 modified "2023-10-14" @default.
- W1517504868 title "Turbine Engine Component Integration" @default.
- W1517504868 doi "https://doi.org/10.1002/9780470686652.eae609" @default.
- W1517504868 hasPublicationYear "2012" @default.
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