Inlet Flow Distortion in an Advanced Civil Transport Boundary Layer Ingesting Engine Installation

This paper presents first-of-a-kind measurements, and complementary computations, of the flow through the propulsion system of a boundary layer ingesting, twin-engine advanced civil transport aircraft configuration. The experiments were carried out in the NASA Langley 14- by 22-foot Subsonic Tunnel, using a 1:11 scale model of the D8 “double-bubble” aircraft with electric ducted fans providing propulsive power. Overall force and moment measurements and flow field surveys at the inlet and nozzle exit planes were obtained. The computations were carried out with the NASA OVERFLOW code. The measurements and computations were conducted for a range of aircraft angles of attack and propulsor powers representing operating points during the aircraft mission. Velocity and pressure distributions at the propulsor inlet and exit, and integral inlet distortion metrics, are presented to quantify the flow non-uniformity due to boundary layer ingestion. The distorted inflow exhibits qualitative and quantitative changes over the mission, from a unidirectional stratified stagnation pressure at cruise to a streamwise vortex structure at climb conditions. The computations capture these flow features and reveal the interactions between airframe and propulsor that create these three-dimensional flow variations.

© 2021, ASME. Originally published in ASME Turbo Expo 2021: Turbomachinery Technical Conference and Exposition.

Files

Metadata

Work Title Inlet Flow Distortion in an Advanced Civil Transport Boundary Layer Ingesting Engine Installation
Access
Open Access
Creators
  1. D. K. Hall
  2. E. M. Greitzer
  3. A. Uranga
  4. M. Drela
  5. S. A. Pandya
License CC BY 4.0 (Attribution)
Work Type Article
Publisher
  1. American Society of Mechanical Engineers
Publication Date June 7, 2021
Publisher Identifier (DOI)
  1. https://doi.org/10.1115/gt2021-59079
Source
  1. Volume 1: Aircraft Engine; Fans and Blowers; Marine; Wind Energy; Scholar Lecture
Deposited April 25, 2022

Versions

Analytics

Collections

This resource is currently not in any collection.

Work History

Version 1
published

  • Created
  • Added GT2021-59079_final_submission-1.pdf
  • Added Creator D. K. Hall
  • Added Creator E. M. Greitzer
  • Added Creator A. Uranga
  • Added Creator M. Drela
  • Added Creator S. A. Pandya
  • Published
  • Updated Description Show Changes
    Description
    • <jats:title>Abstract</jats:title>
    • <jats:p>This paper presents first-of-a-kind measurements, and complementary computations, of the flow through the propulsion system of a boundary layer ingesting, twin-engine advanced civil transport aircraft configuration. The experiments were carried out in the NASA Langley 14- by 22-foot Subsonic Tunnel, using a 1:11 scale model of the D8 “double-bubble” aircraft with electric ducted fans providing propulsive power. Overall force and moment measurements and flow field surveys at the inlet and nozzle exit planes were obtained. The computations were carried out with the NASA OVERFLOW code. The measurements and computations were conducted for a range of aircraft angles of attack and propulsor powers representing operating points during the aircraft mission. Velocity and pressure distributions at the propulsor inlet and exit, and integral inlet distortion metrics, are presented to quantify the flow non-uniformity due to boundary layer ingestion. The distorted inflow exhibits qualitative and quantitative changes over the mission, from a unidirectional stratified stagnation pressure at cruise to a streamwise vortex structure at climb conditions. The computations capture these flow features and reveal the interactions between airframe and propulsor that create these three-dimensional flow variations.</jats:p>
    • This paper presents first-of-a-kind measurements, and complementary computations, of the flow through the propulsion system of a boundary layer ingesting, twin-engine advanced civil transport aircraft configuration. The experiments were carried out in the NASA Langley 14- by 22-foot Subsonic Tunnel, using a 1:11 scale model of the D8 “double-bubble” aircraft with electric ducted fans providing propulsive power. Overall force and moment measurements and flow field surveys at the inlet and nozzle exit planes were obtained. The computations were carried out with the NASA OVERFLOW code. The measurements and computations were conducted for a range of aircraft angles of attack and propulsor powers representing operating points during the aircraft mission. Velocity and pressure distributions at the propulsor inlet and exit, and integral inlet distortion metrics, are presented to quantify the flow non-uniformity due to boundary layer ingestion. The distorted inflow exhibits qualitative and quantitative changes over the mission, from a unidirectional stratified stagnation pressure at cruise to a streamwise vortex structure at climb conditions. The computations capture these flow features and reveal the interactions between airframe and propulsor that create these three-dimensional flow variations.
  • Updated Publisher Identifier (DOI) Show Changes
    Publisher Identifier (DOI)
    • 10.1115/gt2021-59079
    • https://doi.org/10.1115/gt2021-59079