Ses Üstü Hava Alığında Sınır Tabaka – Şok Etkileşiminin Plenum Optimizasyonu ile Kontrolü

Year 2024, , 1269 - 1279, 25.09.2024

Zeliha Türkkahraman , Muhammed Enes Özcan , Buğrahan Alabaş

https://doi.org/10.2339/politeknik.1247300

Cited By: 1

Abstract

Gelişen dünyada özellikle askeri alanlarda süpersonik uçuşların önemi her geçen gün artmaktadır. Ses üstü uçuşlar farklı fiziki şartlara sahip olduğundan ses altı uçaklara göre hem gövde yapısında hem de motor kısmında farklı tasarımlar gerekmektedir. Bu çalışmalarda süpersonik uçuşlar için tasarlanmış jet motorlarının hava giriş performansları araştırılmaktadır. Yüksek basınç geri kazanımı ve düşük akış distorsiyonu hedefine uygun olarak hava giriş geometrisine plenum eklenmiş ve iki aşamalı optimizasyon süreci uygulanarak optimum plenum geometri tasarımı elde edilmiştir. Her bir optimizasyon adımında, plenum tasarımı ve tahliye sisteminin geometrik boyutlarındaki değişikliklerin PR (Basınç Geri Kazanımı) ve FD (Akış Bozulması) değerleri üzerindeki etkilerini belirlemek için hesaplamalı akışkanlar dinamiği analizleri yapılmıştır. Yapılan analiz sonucunda plenum eklentisi ve tahliye sisteminin hava giriş performansına olumlu etkisi olduğu görülmüştür. Optimizasyon süreçleri sonucunda ortaya çıkan yeni plenum tasarımı, hava emişinin performans değerlerini olumlu yönde etkilemiştir. Analiz sonuçları, optimize edilmiş geometride daha yüksek PR ve daha düşük FD sonuçları gösterdi.

Keywords

Supersonic Air Inlet, Optimization, Pressure Recovery

Optimization of Plenum for Control of Boundary Layer-Shock Interaction in Supersonic Inlet

Abstract

In the developing world, the importance of supersonic flights is increasing day by day, especially in military fields. Since supersonic flights have different physical conditions, different designs are required both in the fuselage structure and in the engine part compared to subsonic aircraft. In these studies, the air inlet performance of jet engines designed for supersonic flights is investigated. A plenum has been added to the air inlet geometry in line with the goal of low flow distortion and high pressure recovery. Then, the optimum plenum geometry design was obtained by applying a two-stage optimization process. In each optimization step, computational fluid dynamics analyses were performed to define the effects of the changes in the geometric dimensions of the plenum design and bleed system on the PR (Pressure Recovery) and FD (Flow Distortion) values. The outcome of the analysis showed that the addition of the plenum and the bleed system improved the performance of the air inlet. The new plenum design that emerged as a result of the optimization processes has positively affected the performance values of the air intake. Analysis results showed higher PR and lower FD results in optimized geometry.

Keywords

Supersonic Air Inlet, Optimization, Pressure Recovery

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