Kadir KIRKKÖPRÜ, Murat UYGUN

Katı yakıtlı roket motorlarında daimi olmayan akışların ikili zaman adımlaması yöntemi ile sayısal benzetimi

Değişken iç geometriye sahip katı yakıtlı roket motorlarında iki boyutlu daimi olmayan akışların benzetimi yeni bir kapalı ikili zaman adımlama algoritması kullanılarak gerçekleştirildi. Zamana bağlı denklemler, keyfi Lagrange-Euler sistemi için yazılarak hücre merkezli sonlu hacimler yöntemi ile ayrıklaştırıldı ve yapılı ağlar üzerinde hareketli sınırlar ile çözüldü. Sıkıştırılamaz limitte yakınsama hızını etkileyen akustik ve taşınım hızları arasındaki fark önşartlandırma tekniği ile ortadan kaldırıldı. Yapay sönümleme terimleri düşük Mach sayılarında doğru olarak hesaplanacak şekilde ayarlandı. Önerilen kapalı ikili zaman adımlama algoritmasını kullanan keyfi Lagrange-Euler zaman adımlaması, geometrik korunum yasasını sağlamakta ve hareketsiz ağlarda elde edilen zaman doğruluğunu korumaktadır. Kullanılan keyfi Lagrange-Euler zaman adımlaması, daha az matris çarpımı içermesi ve matris tersinin hesaplanmasını gerektirmediğinden literatürde mevcut olanlara göre daha basittir. Her bir zaman adımında yeni ağ, cebirsel karşısonlu interpolasyon yöntemine dayanan rahatsızlık yöntemi kullanılarak üretildi. Lokal zaman adımlaması, artık düzeltici ve çokluağ yöntemleri kullanılarak yakınsama hızlandırıldı. Katı yakıtlı roket motoru benzeri konfigürasyonda daimi ve daimi olmayan akışların benzetimi hareketsiz ve hareketli ağlar kullanılarak başarı ile yapıldı. Elde edilen hız profilleri, basınç dalgalanmaları ve girdap kopmaları literatürdeki deneysel, analitik ve sayısal sonuçlar ile uyumludur. Hesaplanan sonuçlar, önerilen kapalı zaman algoritması ile geliştirilen akış çözücünün değişken iç geometriye sahip olan katı yakıtlı roket motorlarında iki boyutlu daimi olmayan akışların çözümü ve analizinde kullanılabileceğini göstermektedir.

Numerical simulation of unsteady flows in solid rocket motors with dual time stepping

A computer code, implementing a novel Dual Time Stepping (DTS) algorithm, is developed in order to simulate two-dimensional unsteady cold flow in Solid Rocket Motors (SRM) involving variable internal geometry. Simulation of unsteady flow at allspeeds is essential, since flow speed of combustion gases through an SRM ranges from incompressible limit to supersonic speeds and internal geometry of the SRM varies in time due to regression of combusting propellant surface. In this respect, present code solves compressible form of time dependent conservation laws, written in Arbitrary Lagrangian- Eulerian (ALE) form, on deforming grids at low Mach numbers (M

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