<?xml version="1.0" encoding="utf-8"?>
<export-example>
  <doc>
    <id>32973</id>
    <completedYear/>
    <publishedYear>2024</publishedYear>
    <thesisYearAccepted/>
    <language>eng</language>
    <pageFirst>1</pageFirst>
    <pageLast>20</pageLast>
    <pageNumber/>
    <edition/>
    <issue>6</issue>
    <volume>17</volume>
    <type>articler</type>
    <publisherName/>
    <publisherPlace/>
    <creatingCorporation/>
    <contributingCorporation/>
    <belongsToBibliography>0</belongsToBibliography>
    <completedDate>2024-03-11</completedDate>
    <publishedDate>--</publishedDate>
    <thesisDateAccepted>--</thesisDateAccepted>
    <title language="eng">Film Cooling Modeling in a Turbine Working under the Unsteady Exhaust Flow of Pulsed Detonation Combustion</title>
    <abstract language="eng">Pressure gain combustors (PGCs) have demonstrated significant advantages over conventional combustors in gas turbine engines by increasing the thermal efficiency and reducing the pollution emission level. PGCs use shock waves to transfer energy which contributes to the increase in outlet total pressure. One of the major obstacles in the actual implementation of PGCs in the gas turbine cycle is the exploitation of the highly unsteady flow of the combustor outlet with the downstream turbine. Because of the higher outlet temperature from the PGCs, the turbine blade cooling becomes essential. Due to the highly fluctuating unsteady flow of PGCs, 3D CFD simulation of turbines becomes very expensive. In this work, an alternative approach of using a 1D unsteady Euler model for the turbine is proposed. One of the novel aspects of this paper is to implement the turbine blade cooling in the unsteady 1D Euler model. The main parameters required for the turbine blade cooling are the cooling air mass flow rate, temperature, and pressure. Due to the introduction of coolant flow, the blades are no longer adiabatic and the mass flow rate across the turbine is not constant. Comparing the 1D Euler results against zero-dimensional calculation and 3D CFD approach showed a very good match for both steady and unsteady simulations confirming the applicability of the 1D method.</abstract>
    <parentTitle language="eng">Energies</parentTitle>
    <identifier type="url">https://www.mdpi.com/1996-1073/17/6/1312</identifier>
    <identifier type="doi">10.3390/en17061312</identifier>
    <identifier type="issn">1996-1073</identifier>
    <enrichment key="BTU">an der BTU erstellt / created at BTU</enrichment>
    <enrichment key="Relation">956803</enrichment>
    <enrichment key="BTUfunderName">Marie Skłodowska-Curie</enrichment>
    <enrichment key="Artikelnummer">1312</enrichment>
    <enrichment key="Publikationsweg">Open Access</enrichment>
    <enrichment key="opus.source">publish</enrichment>
    <enrichment key="opus.doi.autoCreate">false</enrichment>
    <enrichment key="opus.urn.autoCreate">false</enrichment>
    <enrichment key="Fprofil">1 Energiewende und Dekarbonisierung / Energy Transition and Decarbonisation</enrichment>
    <author>
      <firstName>Gokkul Raj</firstName>
      <lastName>Varatharajulu Purgunan</lastName>
    </author>
    <submitter>
      <firstName>Majid</firstName>
      <lastName>Asli</lastName>
    </submitter>
    <author>
      <firstName>Majid</firstName>
      <lastName>Asli</lastName>
    </author>
    <author>
      <firstName>Teodosio</firstName>
      <lastName>Nacci</lastName>
    </author>
    <author>
      <firstName>Daniela Anna</firstName>
      <lastName>Misul</lastName>
    </author>
    <author>
      <firstName>Simone</firstName>
      <lastName>Salvadori</lastName>
    </author>
    <author>
      <firstName>Panagiotis</firstName>
      <lastName>Stathopoulos</lastName>
    </author>
    <subject>
      <language>eng</language>
      <type>uncontrolled</type>
      <value>Pressure gain combustion</value>
    </subject>
    <subject>
      <language>eng</language>
      <type>uncontrolled</type>
      <value>Turbomachinery</value>
    </subject>
    <subject>
      <language>eng</language>
      <type>uncontrolled</type>
      <value>Cooling</value>
    </subject>
    <collection role="institutes" number="3503">FG Flug-Triebwerksdesign</collection>
  </doc>
  <doc>
    <id>35082</id>
    <completedYear/>
    <publishedYear>2024</publishedYear>
    <thesisYearAccepted/>
    <language>eng</language>
    <pageFirst>1</pageFirst>
    <pageLast>13</pageLast>
    <pageNumber/>
    <edition/>
    <issue/>
    <volume>Cycle Innovations 2024</volume>
    <type>conferenceobject_ref</type>
    <publisherName>The American Society of Mechanical Engineers</publisherName>
    <publisherPlace/>
    <creatingCorporation/>
    <contributingCorporation>ASME</contributingCorporation>
    <belongsToBibliography>0</belongsToBibliography>
    <completedDate>2025-01-13</completedDate>
    <publishedDate>--</publishedDate>
    <thesisDateAccepted>--</thesisDateAccepted>
    <title language="eng">A Reduced order methodology for optimizing turbine expanders working with rotating detonation combustors</title>
    <abstract language="eng">Redesigning a gas turbine cycle with creative concepts is one of the most critical possibilities for achieving a significant increase in efficiency. Pressure Gain Combustion (PGC) can be used in place of conventional deflagration combustion since PGC contributes to a considerable gain in thermal efficiency while also emitting low NOx levels. One of the major challenges of PGC is the turbine integration to the outlet of the combustor due to the unsteady turbine inflow conditions. This unsteady exhaust flow causes turbomachinery components to operate under fluctuating off-design conditions which in turn, reduces their performance. In this work, the turbine integration to the Rotating Detonation Combustor (RDC) and an optimization methodology for the turbine are discussed. Due to the highly fluctuating unsteady flow of RDC, three-dimensional CFD simulation of turbine becomes very expensive, specifically if it is considered as the objective function evaluator in an optimization process. Thus, an alternative approach of using one-dimensional unsteady Euler model for the turbine is adopted. A two-stage axial turbine is optimized considering unsteady flow features of a hydrogen-air RDC to minimize the entropy generation. When compared to the baseline design, the optimized turbine shows a nearly 2.6% reduction in entropy generation.</abstract>
    <parentTitle language="eng">ASME Turbo Expo 2024: Turbomachinery Technical Conference and Exposition</parentTitle>
    <identifier type="isbn">978-0-7918-8797-4</identifier>
    <identifier type="url">https://asmedigitalcollection.asme.org/GT/proceedings-abstract/GT2024/87974/1204132</identifier>
    <identifier type="doi">10.1115/GT2024-126249</identifier>
    <enrichment key="Fprofil">1 Energiewende und Dekarbonisierung / Energy Transition and Decarbonisation</enrichment>
    <enrichment key="BTU">an der BTU erstellt / created at BTU</enrichment>
    <enrichment key="Relation">956803</enrichment>
    <enrichment key="BTUfunderName">European Union’s Horizon 2020 research and innovation programme - Marie Skłodowska-Curie</enrichment>
    <enrichment key="Artikelnummer">GT2024-126249</enrichment>
    <enrichment key="opus.source">publish</enrichment>
    <enrichment key="opus.doi.autoCreate">false</enrichment>
    <enrichment key="opus.urn.autoCreate">false</enrichment>
    <author>
      <firstName>Gokkul Raj Varatharajulu</firstName>
      <lastName>Purgunan</lastName>
    </author>
    <submitter>
      <firstName>Majid</firstName>
      <lastName>Asli</lastName>
    </submitter>
    <author>
      <firstName>Majid</firstName>
      <lastName>Asli</lastName>
    </author>
    <author>
      <firstName>Roman</firstName>
      <lastName>Klopsch</lastName>
    </author>
    <author>
      <firstName>Josh</firstName>
      <lastName>Meister</lastName>
    </author>
    <author>
      <firstName>Panagiotis</firstName>
      <lastName>Stathopoulos</lastName>
    </author>
    <subject>
      <language>eng</language>
      <type>uncontrolled</type>
      <value>Pressure gain combustion</value>
    </subject>
    <subject>
      <language>eng</language>
      <type>uncontrolled</type>
      <value>Turbomachinery</value>
    </subject>
    <collection role="institutes" number="3503">FG Flug-Triebwerksdesign</collection>
  </doc>
</export-example>
