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Model Turbojet Engine: Numerical Inv...

Barraza, Bryan.

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Model Turbojet Engine: Numerical Investigation of Flow Through Turbine Cascade and Afterburner Design.

Record Type:	Electronic resources : Monograph/item
Title/Author:	Model Turbojet Engine: Numerical Investigation of Flow Through Turbine Cascade and Afterburner Design./
Author:	Barraza, Bryan.
Published:	Ann Arbor : ProQuest Dissertations & Theses, : 2020,
Description:	69 p.
Notes:	Source: Masters Abstracts International, Volume: 81-12.
Contained By:	Masters Abstracts International81-12.
Subject:	Aerospace engineering. -
Online resource:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=27955078
ISBN:	9798645475390

Model Turbojet Engine: Numerical Investigation of Flow Through Turbine Cascade and Afterburner Design.
Barraza, Bryan.

Model Turbojet Engine: Numerical Investigation of Flow Through Turbine Cascade and Afterburner Design. - Ann Arbor : ProQuest Dissertations & Theses, 2020 - 69 p.

Source: Masters Abstracts International, Volume: 81-12.

Thesis (M.S.)--New Mexico State University, 2020.

This item must not be sold to any third party vendors.

Small model airplane jet engines can have an outer diameter of less than four inches and can spin at more than 100,000 revolutions per minute. Under such conditions, the rotational effects are expected to be considerably stronger than for larger commercial engines. To increase the thrust of a small turbojet engine, an afterburner was designed. The design was based on a Parametric Cycle Analysis and an ANSYS FLUENT simulation to analyze the flow and ignition in the afterburner. Moreover, to investigate how rotation affects the mean flow, numerical simulations were performed of a linear and annular low-pressure turbine cascade for a Reynolds number of Re = 5,000. For these simulations, terms accounting for the Coriolis and centrifugal accelerations were added to the right-hand side of an existing Navier-Stokes code. Simulations were performed without and with rotational effects. The parameters for the latter were chosen to model a small model engine and a larger military engine. A comparison of the results obtained from the simulations revealed several interesting differences: The rotational effects were found to cause a spanwise pressure gradient and a noticeably asymmetric suction surface skin-friction line topology. In particular, the passage vortex on the inboard side was much stronger than for the case without rotation and the passage vortex on the outboard side was missing.

ISBN: 9798645475390Subjects--Topical Terms:

1002622
Aerospace engineering.
Subjects--Index Terms:

Aerospace

Model Turbojet Engine: Numerical Investigation of Flow Through Turbine Cascade and Afterburner Design.
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100 1 $a Barraza, Bryan. $3 3550778
245 1 0 $a Model Turbojet Engine: Numerical Investigation of Flow Through Turbine Cascade and Afterburner Design.
260 1 $a Ann Arbor : $b ProQuest Dissertations & Theses, $c 2020
300 $a 69 p.
500 $a Source: Masters Abstracts International, Volume: 81-12.
500 $a Advisor: Gross, Andreas.
502 $a Thesis (M.S.)--New Mexico State University, 2020.
506 $a This item must not be sold to any third party vendors.
520 $a Small model airplane jet engines can have an outer diameter of less than four inches and can spin at more than 100,000 revolutions per minute. Under such conditions, the rotational effects are expected to be considerably stronger than for larger commercial engines. To increase the thrust of a small turbojet engine, an afterburner was designed. The design was based on a Parametric Cycle Analysis and an ANSYS FLUENT simulation to analyze the flow and ignition in the afterburner. Moreover, to investigate how rotation affects the mean flow, numerical simulations were performed of a linear and annular low-pressure turbine cascade for a Reynolds number of Re = 5,000. For these simulations, terms accounting for the Coriolis and centrifugal accelerations were added to the right-hand side of an existing Navier-Stokes code. Simulations were performed without and with rotational effects. The parameters for the latter were chosen to model a small model engine and a larger military engine. A comparison of the results obtained from the simulations revealed several interesting differences: The rotational effects were found to cause a spanwise pressure gradient and a noticeably asymmetric suction surface skin-friction line topology. In particular, the passage vortex on the inboard side was much stronger than for the case without rotation and the passage vortex on the outboard side was missing.
590 $a School code: 0143.
650 4 $a Aerospace engineering. $3 1002622
650 4 $a Fluid mechanics. $3 528155
650 4 $a Thermodynamics. $3 517304
653 $a Aerospace
653 $a Afterburner
653 $a Computational fluid dynamics
653 $a Turbomachinery
690 $a 0538
690 $a 0204
690 $a 0348
710 2 $a New Mexico State University. $b Mechanical and Aerospace Engineering. $3 3540154
773 0 $t Masters Abstracts International $g 81-12.
790 $a 0143
791 $a M.S.
792 $a 2020
793 $a English
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=27955078