A Parametric and Performance-Based CFD Investigation Of The Effect Of Cavity Geometry and Location Of Injector On Flame Stabilization In Supersonic Flow

Barış Akın; Mohammad Alobeid; Ahmed Emin Kılıç

Article Details

A Parametric and Performance-Based CFD Investigation Of The Effect Of Cavity Geometry and Location Of Injector On Flame Stabilization In Supersonic Flow

Authors:

Barış Akın | Mohammad Alobeid | Ahmed Emin Kılıç

Publisher:

Ankara Yildirim Beyazit University

Main Topics:

Akışkan Akışı | Isı ve Kütle Transferinde Hesaplamalı Yöntemler (Hesaplamalı Akışkanlar Dinamiği Dahil)

Journal:

International Journal of Energy Horizon (IJEH) Vol.1 Issue 1, pp.1-7

Document Type:

Article

Publication Date:

6/2025

Document Language:

English

Document ID (Org No.):

2001353600

pISSN:

3108-3722

Keywords:

Abstract:

 Scramjet Supersonic Combustion Ramjet engines are a key propulsion technology for hypersonic flight, where stable combustion and efficient fuelair mixing under supersonic conditions remain fundamental challenges. This study presents a two-dimensional computational fluid dynamics CFD investigation to optimize cavity geometry and fuel injection configurations in a scramjet combustor to enhance mixing and flame stabilization. Rectangular and trapezoidal cavity geometries were assessed under varying hydrogen injection pressures 1, 2, and 3 atm and locations top, middle, and bottom using ANSYS Fluent. A density-based solver incorporating the SST k-ω turbulence model and the Eddy Dissipation Model was employed to simulate reactive flow dynamics. Validation of the numerical model was performed through comparison with experimental data, ensuring mesh independence and agreement on normalized pressure profiles. Results showed that injection location and cavity geometry significantly influence flow recirculation, fuel retention, and temperature distribution. The middle injection at 2 atm in the rectangular cavity yielded the most uniform vortex formation and highest combustion efficiency. In contrast, top injection configurations consistently resulted in poor flame holding due to bypassing of the cavity. For the trapezoidal cavity, middle and bottom injections at 2 atm exhibited comparable mixing behavior, albeit with lower peak temperatures. Overall, the rectangular cavity with centerline injection at 2 atm demonstrated optimal performance for sustained combustion in supersonic flow. These findings contribute to the design of efficient flameholders in scramjet systems, offering insights for improved performance in future hypersonic propulsion applications.

 Scramjet Supersonic Combustion Ramjet engines are a key propulsion technology for hypersonic flight, where stable combustion and efficient fuelair mixing under supersonic conditions remain fundamental challenges. This study presents a two-dimensional computational fluid dynamics CFD investigation to optimize cavity geometry and fuel injection configurations in a scramjet combustor to enhance mixing and flame stabilization. Rectangular and trapezoidal cavity geometries were assessed under varying hydrogen injection pressures 1, 2, and 3 atm and locations top, middle, and bottom using ANSYS Fluent. A density-based solver incorporating the SST k-ω turbulence model and the Eddy Dissipation Model was employed to simulate reactive flow dynamics. Validation of the numerical model was performed through comparison with experimental data, ensuring mesh independence and agreement on normalized pressure profiles. Results showed that injection location and cavity geometry significantly influence flow recirculation, fuel retention, and temperature distribution. The middle injection at 2 atm in the rectangular cavity yielded the most uniform vortex formation and highest combustion efficiency. In contrast, top injection configurations consistently resulted in poor flame holding due to bypassing of the cavity. For the trapezoidal cavity, middle and bottom injections at 2 atm exhibited comparable mixing behavior, albeit with lower peak temperatures. Overall, the rectangular cavity with centerline injection at 2 atm demonstrated optimal performance for sustained combustion in supersonic flow. These findings contribute to the design of efficient flameholders in scramjet systems, offering insights for improved performance in future hypersonic propulsion applications.

 Scramjet Supersonic Combustion Ramjet engines are a key propulsion technology for hypersonic flight, where stable combustion and efficient fuelair mixing under supersonic conditions remain fundamental challenges. This study presents a two-dimensional computational fluid dynamics CFD investigation to optimize cavity geometry and fuel injection configurations in a scramjet combustor to enhance mixing and flame stabilization. Rectangular and trapezoidal cavity geometries were assessed under varying hydrogen injection pressures 1, 2, and 3 atm and locations top, middle, and bottom using ANSYS Fluent. A density-based solver incorporating the SST k-ω turbulence model and the Eddy Dissipation Model was employed to simulate reactive flow dynamics. Validation of the numerical model was performed through comparison with experimental data, ensuring mesh independence and agreement on normalized pressure profiles. Results showed that injection location and cavity geometry significantly influence flow recirculation, fuel retention, and temperature distribution. The middle injection at 2 atm in the rectangular cavity yielded the most uniform vortex formation and highest combustion efficiency. In contrast, top injection configurations consistently resulted in poor flame holding due to bypassing of the cavity. For the trapezoidal cavity, middle and bottom injections at 2 atm exhibited comparable mixing behavior, albeit with lower peak temperatures. Overall, the rectangular cavity with centerline injection at 2 atm demonstrated optimal performance for sustained combustion in supersonic flow. These findings contribute to the design of efficient flameholders in scramjet systems, offering insights for improved performance in future hypersonic propulsion applications.

 Scramjet Süpersonik Yanmalı Ramjet motorları, süpersonik koşullar altında kararlı yanma ve verimli yakıt-hava karışımının temel zorluklar olmaya devam ettiği hipersonik uçuş için önemli bir itici güç teknolojisidir. Bu çalışma, karıştırma ve alev stabilizasyonunu geliştirmek için bir scramjet yakıcıdaki boşluk geometrisini ve yakıt enjeksiyon konfigürasyonlarını optimize etmek için iki boyutlu bir hesaplamalı akışkanlar dinamiği CFD araştırması sunmaktadır. Dikdörtgen ve trapez boşluk geometrileri, ANSYS Fluent kullanılarak değişen hidrojen enjeksiyon basınçları 1, 2 ve 3 atm ve konumları üst, orta ve alt altında değerlendirilmiştir. Reaktif akış dinamiklerini simüle etmek için SST k-ω türbülans modelini ve Eddy Dissipation Modelini içeren yoğunluk tabanlı bir çözücü kullanılmıştır. Sayısal modelin doğrulanması, ağ bağımsızlığı ve normalleştirilmiş basınç profilleri üzerinde uyum sağlanarak deneysel verilerle karşılaştırılarak gerçekleştirilmiştir. Sonuçlar, enjeksiyon konumu ve boşluk geometrisinin akış devridaimini, yakıtın tutulmasını ve sıcaklık dağılımını önemli ölçüde etkilediğini göstermiştir. Dikdörtgen boşlukta 2 atmde orta enjeksiyon en düzgün girdap oluşumunu ve en yüksek yanma verimliliğini sağlamıştır. Buna karşılık, üst enjeksiyon konfigürasyonları, boşluğun baypas edilmesi nedeniyle sürekli olarak zayıf alev tutma ile sonuçlanmıştır. Trapez kavite için, 2 atmdeki orta ve alt enjeksiyonlar, daha düşük tepe sıcaklıkları olsa da, benzer karıştırma davranışı sergilemiştir. Genel olarak, 2 atmde orta hat enjeksiyonlu dikdörtgen kavite, süpersonik akışta sürekli yanma için optimum performans göstermiştir. Bu bulgular, scramjet sistemlerinde verimli alev tutucuların tasarımına katkıda bulunmakta ve gelecekteki hipersonik tahrik uygulamalarında daha iyi performans için içgörüler sunmaktadır.

Article Details

A Parametric and Performance-Based CFD Investigation Of The Effect Of Cavity Geometry and Location Of Injector On Flame Stabilization In Supersonic Flow

Authors:

Barış Akın | Mohammad Alobeid | Ahmed Emin Kılıç

Publisher:

Ankara Yildirim Beyazit University

Main Topics:

Akışkan Akışı | Isı ve Kütle Transferinde Hesaplamalı Yöntemler (Hesaplamalı Akışkanlar Dinamiği Dahil)

Journal:

International Journal of Energy Horizon (IJEH) Vol.1 Issue 1, pp.1-7

Document Type:

Article

Publication Date:

6/2025

Document Language:

English

Document ID (Org No.):

2001353600

pISSN:

3108-3722

Scramjet Combustion

Cavity Geometry

Fuel Injection Location

Flame Stabilization

CFD SimulationScramjet Yanması

Boşluk Geometrisi

Yakıt Enjeksiyon Konumu

Alev Stabilizasyonu

CFD Simülasyonu

Issues

Article Details

Authors: Barış Akın | Mohammad Alobeid | Ahmed Emin Kılıç

Publisher: Ankara Yildirim Beyazit University

Main Topics: Akışkan Akışı | Isı ve Kütle Transferinde Hesaplamalı Yöntemler (Hesaplamalı Akışkanlar Dinamiği Dahil)

Journal: International Journal of Energy Horizon (IJEH) Vol.1 Issue 1, pp.1-7

Document Type: Article

Publication Date: 6/2025

Document Language: English

Document ID (Org No.): 2001353600

pISSN: 3108-3722

Issues

Authors:

Barış Akın | Mohammad Alobeid | Ahmed Emin Kılıç

Publisher:

Ankara Yildirim Beyazit University

Main Topics:

Akışkan Akışı | Isı ve Kütle Transferinde Hesaplamalı Yöntemler (Hesaplamalı Akışkanlar Dinamiği Dahil)

Journal:

International Journal of Energy Horizon (IJEH) Vol.1 Issue 1, pp.1-7

Document Type:

Article

Publication Date:

6/2025

Document Language:

English

Document ID (Org No.):

2001353600

pISSN:

3108-3722