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| Content Provider | The American Society of Mechanical Engineers (ASME) Digital Collection |
|---|---|
| Author | Goldberg, Chana Nalianda, Devaiah Pilidis, Pericles |
| Copyright Year | 2017 |
| Abstract | Conventional propulsion systems are typically represented as uninstalled system to suit the simple separation between airframe and engine in a podded configuration. However, boundary layer ingesting systems are inherently integrated, and require a different perspective for performance analysis. Simulations of boundary layer ingesting propulsions systems must represent the change in inlet flow characteristic which result from the local flow condition. In addition, a suitable accounting system is required to split the airframe forces from the propulsion system forces. The research assesses the performance of a conceptual vehicle which applies a boundary layer ingesting propulsion system — NASA’s N3-X blended wing body aircraft — as a case study. The performance of the aircraft’s distributed propulsor array is assessed using a performance method which accounts for installation terms resulting from the boundary layer ingesting nature of the system. A ‘thrust split’ option is considered which splits the source of thrust between the aircraft’s main turbojet engines and the distributed propulsor array. An optimum thrust split for a specific fuel consumption at cruise is found to occur for a thrust split value of 93%, for the configuration considered. In comparison, the optimum thrust split with respect to fuel consumption for the design 7500 nmi mission is found to be 91.5%. Aircraft performance estimates suggest the N3-X could achieve a maximum payload range of approximately 13650 nautical miles. |
| Sponsorship | International Gas Turbine Institute |
| File Format | |
| ISBN | 9780791850831 |
| DOI | 10.1115/GT2017-63917 |
| Volume Number | Volume 3: Coal, Biomass and Alternative Fuels; Cycle Innovations; Electric Power; Industrial and Cogeneration Applications; Organic Rankine Cycle Power Systems |
| Conference Proceedings | ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition |
| Language | English |
| Publisher Date | 2017-06-26 |
| Publisher Place | Charlotte, North Carolina, USA |
| Access Restriction | Subscribed |
| Subject Keyword | Accounting Fuel consumption Separation (technology) Flow (dynamics) Engines Vehicles Design Wings Simulation Turbojets Engineering simulation Propulsion systems Aircraft Boundary layers Thrust |
| Content Type | Text |
| Resource Type | Article |
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