أسامة الأخضر
23-07-2008, 02:15 PM
السلم عليكم يا مهندسين العرب أرجو منكم المساعدة في ترجمة هذه الورقة إلي اللغة العربية ولكم مني جزيل الشكر وهذا أيميلي alakder_10@yahoo.com
4.3 Compressor Design Approach
As it was explained in Chapter 3, and having decided up on the engine design point parameters, the next step is designing the various components of the engine. This chapter, therefore, covers the axial flow compressor aerodynamic design. The compressor mechanical design is beyond the scope of this project. In general, the compressor aerodynamic design should include the following stages:
Determination of amiulus geometry and stage velocity triangles for design point operation.
Compressor blading.
Prediction of compressor off-design performance.
However, throughout this project only determination of annulus geometry and stage velocity triangles for design point operation will be discussed in some details. An attempt was made to develop a FORTRAN program to carry out a pitch line compressor aerodynamic design and velocity triangles calculations at the root, blade mid height (BMH) and at the tip of the compressor blades. The results of this program were very satisfying and are summarized in table 4.1.
4.3 Compressor Design Approach
As it was explained in Chapter 3, and having decided up on the engine design point parameters, the next step is designing the various components of the engine. This chapter, therefore, covers the axial flow compressor aerodynamic design. The compressor mechanical design is beyond the scope of this project. In general, the compressor aerodynamic design should include the following stages:
Determination of amiulus geometry and stage velocity triangles for design point operation.
Compressor blading.
Prediction of compressor off-design performance.
However, throughout this project only determination of annulus geometry and stage velocity triangles for design point operation will be discussed in some details. An attempt was made to develop a FORTRAN program to carry out a pitch line compressor aerodynamic design and velocity triangles calculations at the root, blade mid height (BMH) and at the tip of the compressor blades. The results of this program were very satisfying and are summarized in table 4.1.