Versatile Adaptive Micro Turbofan Engine Development for UAS Applications

Abstract

The goal of our project is the development of a variable cycle micro gas turbine engine, which operates via integration of a fan by a fixed gear transmission into an existing micro-turbojet with an adaptive bypass nozzle. The developed solution significantly improves maximum thrust, reduces fuel consumption by maintaining the core independently running at its optimum, and enables a wider operational range, all the meanwhile preserving a simple single spool configuration.

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Document Details

Document Type
Technical Report
Publication Date
Sep 28, 2021
Accession Number
AD1154923

Entities

People

  • Beni Cukurel
  • David Linsky
  • Michael Palman
  • Sercan Acarer

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Abstracts
  • Assembly
  • Availability
  • Bearings
  • Classification
  • Engine Components
  • Engines
  • Flow Rate
  • Friction
  • Fuel Consumption
  • Gas Turbines
  • Gears
  • Heat Transfer
  • Instrumentation
  • Jet Aircraft
  • Jet Engines
  • Load Cells
  • Manufacturing
  • Measurement
  • Monitoring
  • Propulsion Systems
  • Static Pressure
  • Test Stands
  • Thermodynamic Cycles
  • Turbofan Engines
  • Turbojet Engines

Readers

  • Aerospace Engineering
  • Systems Analysis and Design