Dahili Hava Soğutmalı Gaz Türbini Kanatçıkları için 2.5D Kafes Yapılarının Tasarımı ve Sonlu Elemanlar Analizi

Abstract

Malzeme özelliklerini değiştirmeden hafif tasarımlar yapmak, havacılık için çok önemlidir. Ayrıca, yüksek sıcaklıklarda çalışan metal jet motoru parçalarının, örneğin gaz türbini kanatçıklarının etkili bir şekilde soğutulması, motor verimliliğini artırmak ve gaz türbini kanatçıklarının ömrünü uzatmak için gereklidir. Bu bağlamda, eklemeli imalat alanındaki gelişmelerle paralel olarak, hem önemli ölçüde ağırlık azaltımı sağlayan hem de etkili soğutma için büyük yüzey alanı sunan kafes yapılar, son zamanlarda oldukça popüler bir konu haline gelmiştir. Bu çalışmada, iç hava soğutmalı gaz türbini kanaçıkları için kare, üçgen ve altıgen 2.5D kafes yapıları tasarlanmış ve sonlu elemanlar yöntemi ile analiz edilmiştir. Hava soğutma kanallarına sahip geleneksel bir gaz türbini kanadı referans olarak kullanılmıştır. Sonuçlar, kafes tasarımları sayesinde gaz türbini kanadında %17,14'e kadar ağırlık azaltımı ve %93,43'e kadar hava soğutma yüzeyi artışı sağlanabileceğini göstermiştir. Maksimum gerilme, güvenlik faktörü (FOS) ve deformasyon gibi sonuçlar ile birlikte ağırlık azaltımı ve yüzey alanı artışı değerlendirildiğinde, en uygun 2.5D kafes tasarımının altıgen olduğu sonucuna varılmıştır.

Keywords

• Kafes yapısı;
• türbin kanatçığı;
• Inconel 718
• sonlu elemanlar analizi;
• mekanik özellikler;
• ağırlık azaltımı

Design And Finite Element Analysis Of 2.5D Lattice Structures For Internal Air-Cooled Gas Turbine Blades

Abstract

Making lightweight designs without changing the properties of materials is very important for aviation. In addition, effective cooling of metallic jet engine parts operating at high temperatures, such as gas turbine blades, is necessary to increase the efficiency of the engine and extend the service life of the gas turbine blade. In this regard, in parallel with the developments in additive manufacturing, lattice structures that provide both significant weight reduction and large surface area for effective cooling have recently started to be a hot topic. In this study, square, triangular and hexagonal 2.5D lattice structures were designed for the internal air-cooled gas turbine blade and analyzed by the finite element method. A conventional gas turbine blade with air cooling channels was used as a reference. The results showed that up to 17.14% weight reduction and up to 93.43% air cooling surface area increase can be achieved in the gas turbine blade thanks to lattice designs. When the results of maximum stress, FOS and deformation in turbine blades, as well as weight reduction and surface area increase, were evaluated together, it was concluded that the most suitable 2.5D lattice design was hexagonal.

Keywords

• Lattice structure;
• turbine blade;
• Inconel 718;
• finite element analysis;
• mechanical properties;
• weight reduction

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