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Design and Evaluation of a Thermal Nozzle for Small-Scale Turbojets.

Record Type:	Electronic resources : Monograph/item
Title/Author:	Design and Evaluation of a Thermal Nozzle for Small-Scale Turbojets./
Author:	Braun, Joshua Robert.
Description:	1 online resource (86 pages)
Notes:	Source: Masters Abstracts International, Volume: 84-07.
Contained By:	Masters Abstracts International84-07.
Subject:	Aerospace engineering. -
Online resource:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=29164389click for full text (PQDT)
ISBN:	9798363509483

Design and Evaluation of a Thermal Nozzle for Small-Scale Turbojets.
Braun, Joshua Robert.

Design and Evaluation of a Thermal Nozzle for Small-Scale Turbojets. - 1 online resource (86 pages)

Source: Masters Abstracts International, Volume: 84-07.

Thesis (M.S.)--Oklahoma State University, 2022.

Includes bibliographical references

This paper presents the design and evaluation of a thermal nozzle for small-scale turbojets. Historically, small-scale turbojets have suffered from poor thermal efficiency and thrust specific fuel consumption (TSFC). This is primarily because their small geometry limits the compressor pressure ratio from reaching higher values, which directly impacts TSFC. An alternative approach to improving TSFC is to preheat the fuel before it enters the combustion chamber. This will add enthalpy to the flow, thus reducing the amount of fuel required to the reach the same turbine inlet temperature. The thermal nozzle presented in this study achieves this by acting as a heat exchanger between the hot exhaust gas and the fuel before it enters the engine.Computational fluid dynamics (CFD) and preliminary experiments were used to guide the design of the nozzle, where key considerations included pressure drop, fuel temperature limits, and manufacturability. Parameters such as channel geometry and thickness were varied and analyzed to arrive at a final design that met the design goals. A 70 lbf KingTech K320 turbojet was chosen to evaluate the performance of the thermal nozzle. Analytical evaluation was performed using an ε-NTU heat exchanger model calibrated from CFD results, parametric cycle analysis, and engine performance analysis. Analysis shows a TSFC improvement of 2.07% at full throttle. However, the heat that is recuperated in the nozzle slightly reduces the thrust output of the engine, where analysis for specific thrust shows a decrease of 0.48% at full throttle.

Electronic reproduction.
Ann Arbor, Mich. :
ProQuest,
2023

Mode of access: World Wide Web

ISBN: 9798363509483Subjects--Topical Terms:

1002622
Aerospace engineering.
Subjects--Index Terms:

Computational fluid dynamicsIndex Terms--Genre/Form:

542853
Electronic books.

Design and Evaluation of a Thermal Nozzle for Small-Scale Turbojets.
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100 1 $a Braun, Joshua Robert. $3 3704053
245 1 0 $a Design and Evaluation of a Thermal Nozzle for Small-Scale Turbojets.
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300 $a 1 online resource (86 pages)
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500 $a Source: Masters Abstracts International, Volume: 84-07.
500 $a Advisor: Rouser, Kurt.
502 $a Thesis (M.S.)--Oklahoma State University, 2022.
504 $a Includes bibliographical references
520 $a This paper presents the design and evaluation of a thermal nozzle for small-scale turbojets. Historically, small-scale turbojets have suffered from poor thermal efficiency and thrust specific fuel consumption (TSFC). This is primarily because their small geometry limits the compressor pressure ratio from reaching higher values, which directly impacts TSFC. An alternative approach to improving TSFC is to preheat the fuel before it enters the combustion chamber. This will add enthalpy to the flow, thus reducing the amount of fuel required to the reach the same turbine inlet temperature. The thermal nozzle presented in this study achieves this by acting as a heat exchanger between the hot exhaust gas and the fuel before it enters the engine.Computational fluid dynamics (CFD) and preliminary experiments were used to guide the design of the nozzle, where key considerations included pressure drop, fuel temperature limits, and manufacturability. Parameters such as channel geometry and thickness were varied and analyzed to arrive at a final design that met the design goals. A 70 lbf KingTech K320 turbojet was chosen to evaluate the performance of the thermal nozzle. Analytical evaluation was performed using an ε-NTU heat exchanger model calibrated from CFD results, parametric cycle analysis, and engine performance analysis. Analysis shows a TSFC improvement of 2.07% at full throttle. However, the heat that is recuperated in the nozzle slightly reduces the thrust output of the engine, where analysis for specific thrust shows a decrease of 0.48% at full throttle.
533 $a Electronic reproduction. $b Ann Arbor, Mich. : $c ProQuest, $d 2023
538 $a Mode of access: World Wide Web
650 4 $a Aerospace engineering. $3 1002622
650 4 $a Mechanical engineering. $3 649730
650 4 $a Thermodynamics. $3 517304
653 $a Computational fluid dynamics
653 $a Thermal nozzle performance
653 $a Thrust specific fuel consumption
653 $a Small-scale turbojets
655 7 $a Electronic books. $2 lcsh $3 542853
690 $a 0538
690 $a 0548
690 $a 0348
710 2 $a ProQuest Information and Learning Co. $3 783688
710 2 $a Oklahoma State University. $b Mechanical & Aerospace Engineering. $3 3194223
773 0 $t Masters Abstracts International $g 84-07.
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=29164389 $z click for full text (PQDT)