Effect Of Temperature Distribution In 10c4/60c50 Gas Turbine Blade Model Using Finite Element Analysis

Effect Of Temperature Distribution In 10c4/60c50 Gas Turbine Blade Model Using Finite Element Analysis

V.Veeraragavan

Lecturer in Mechanical Engineering

Eritrea Institute of Technology, Asmara, Eritrea, N.E.Africa

Abstract

In this research paper is mainly apprehensive with aircraft gas turbine engine. Turbine blade is an important part of aircraft gas turbine engine. The research focus of 10 C4 / 60 C 50 turbine blade model, because of its common use in all types of aircraft engines. Investigate used, Pro-e model and ANSYS tools. Present research was focused on using Finite element methods (FEM) to predict the location of possible temperature areas on turbine blades. The conventional alloys such as titanium, zirconium, molybdenum, super alloys are chosen for analysis. Initially the model is created with the help of Pro-e and then it is imported to Ansys.The static analysis of solid model is carried out by applying temperature from external circumference tip of turbine blade to root of the blade and the temperature distribution is plotted. At that time measured the maximum temperature withstood capacity in gas turbine blade. Finally the entire four alloy materials are compared with respect to temperature distribution to found out of the best one. Then suggested to which material is better performing in gas turbine engine applications.

Keywords: Gas turbine, Titanium, Temperature Distribution, Turbine blade, Rotor.

1. Introduction

   Gas turbines play an important role in aviation and industrial applications. There is a growing tendency to use higher temperatures at the inlet of the turbine to improve the efficiency of the

   gas turbine engine. Consequently the heat load on the turbine components increases, especially in the high pressure turbine section. This heat load is caused by the exposure of an enormous heat flux of the burnt gas from the combustion chamber. Turbine blades are one of the most important components in a gas turbine application. There are components across which flow of high pressure gases takes place to produce work. A blade can be defined as the medium of transfer of energy from the gases to the turbine rotor. For turbine blades, however, stresses due to aerodynamic forces are typically much less important than stresses due to centrifugal loads. The same is not necessarily true to thermal stresses. If blade temperature is non- uniform (as it may well be, if exposed to a gas 400°C to 500°C better than the blade and subject to intense inner cooling through a distribution of air passages), it can suffer fairly large thermal stresses. A gas turbine is similar to the steam turbine but gas is used to run the turbine. It is mainly used in the aircraft engines, electric power generation, marine propulsion etc. Damage to turbine blades is of critical importance in aircraft engines. The irregular movements of throttle settings are a mandatory requirement for the pilots to perform various air combat maneuvers. This leads to excessive stresses on engine compressor and turbine blades in various flight regimes. The aircraft are also required to fly in varying atmospheric conditions ranging from negative temperature in icing conditions to over 50 degree Celsius in summers. These factors in addition to operations from deserts and tropical weathers also add to the variety of conditions that an aircraft engine is exposed.

2. Materials

   1. Titanium Alloys

      Table-1: Composition

      Composition	Weight Percentage
      Aluminum (A1)	8
      Molybdenum (M0)	1
      Titanium (Ti)	90
      Vanadium (VD)	1

      Table-2: Properties

      Density	4370 kg/m3
      Yield Strength	1070 Mpa
      Ultimate Strength	1180 Mpa
      Poisson Ratio	0.32
      Youngs Modules	120 Gpa
      Melting Pont	15400 C
      Thermal Expansion	0.000010/m0 C
      Thermal Conductivity	600 W/mk
      Specific Heat	502 J/Kg k

   2. Zirconium Alloys

      Table-3: Composition

      Composition	Weight Percentage
      Iron + Chromium ( Fe + Cr )	0.2
      Hafinium (Hf )	Max 4.5
      Niobium (Nb)	2.5
      Oxygen (O)	0.18
      Zirconium (Zr)	Min 95.5

      Table-4: Properties

      Density	6640 Kg/m3
      Yield Strength	582 Mpa
      Ultimate Strength	750 MPa
      Poisson Ratio	0.33
      Youngs Modules	97.9 Gpa
      Melting Pont	17400 C
      Thermal Expansion	0.0000063 /m0 C
      Thermal Conductivity	17 W/ m k
      Specific Heat	285 J/Kg0 C

   3. Molybdenum Alloys

      Table-5: Composition

      Composition	Weight Percentage
      Molybdenum (Mo)	52.5%
      Rhenium (Rh)	47.5%

      Table-6: Properties

      Density	9320 Kg/m3
      Yield Strength	845 Mpa
      Ultimate Strength	1180 Mpa
      Youngs Modules	365 Gpa
      Poisson Ratio	0.285
      Thermal Expansion (at 10000C)	6.45 m/m0C
      Thermal Conductivity	36.8 W/ m k
      Specific Heat	255 J/Kg0 C
      Melting Point	24500C

   4. Super Alloys

   Table-7: Composition

   Composition	Weight Percentage
   Nickel Base (Ni)	78%
   Chromium (Cr)	20%
   Titanium (Ti)	0.4%
   Carbon (c)	0.12%

   Table-8: Properties

   Density	8526 Kg/m3
   Yield Strength	855 Mpa
   Youngs Modules	220 Gpa
   Poisson Ratio	0.33
   Melting Pont	8700 C
   Thermal Expansion	15.8 micron/m.k
   Thermal Conductivity	24.9 W/ m k
   Specific Heat	525 J/Kg0 k

3. Modeling and Analysis

   Pro/Engineer is a solid modeling software and it develops models as solid, allowing to work in a three dimensional environment. These models have volume and surface area, so you can calculate the mass propertis directly from the geometry that you can create and manipulate their display on the screen, the models remain as solids. To truly

   appreciate the power of Pro/ Engineer as a solid modeling tool, you must a quire an understanding of the following concepts: feature based, associative and parametric modeling. Then after creating a model, imported to ansys and mesh the model. After that applying all properties of materials in ansys and temperature graph plotted.

4. Results and Discussion

   Fig-1. Temperature Propagation for Titanium Alloy.

   Fig-1 shows show that, blue color curve to represent the temperature from root of the blade. The red color curve to represent the external circumference tip of turbine blade.Hence,during that time of 20 seconds corresponding to the temperature will reaches 140° C in root of the blade and 390 ° C in external circumference tip of turbine blade respectively.

   Fig-2. Temperature Propagation for Zirconium Alloy.

   Fig-2 shows show that, blue color curve to represent the temperature from root of the blade. The red color curve to represent the external circumference tip of turbine

   blade.Hence,during that time of 20 seconds corresponding to the temperature will reaches 290° C in root of the blade and 450 ° C in external circumference tip of turbine blade respectively.

   Fig-3. Temperature Propagation for Molybdenum Alloy

   Fig-3 shows show that, blue color curve to represent the temperature from root of the blade. The red color curve to represent the external circumference tip of turbine blade.Hence,during that time of 20 seconds corresponding to the temperature will reaches 35° C in root of the blade and 190 ° C in external circumference tip of turbine blade respectively.

   Fig-4.Temperature Propagation for Super Alloy.

   Fig-4 shows show that, blue color curve to represent the temperature from root of the blade. The red color curve to represent the external circumference tip of turbine blade.Hence,during that time of 20 seconds corresponding to the temperature will reaches 345° C in root of the blade and 460 ° C in external circumference tip of turbine blade respectively.

5. Conclusion

The comparisons of temperature distribution of four alloys graphs are shows that, a first one titanium alloy temperature at 20 sec to reached temperature at 390°C.Second one zirconium alloy temperature at 20 sec to reached temperature at 450°C.Third one molybdenum alloy temperature at 20 sec to reached temperature at 190°C.Fourth one super alloys temperature at 20 sec to reached temperature reached at 460°C. Hence, these four alloys temperature comparatives are state that molybdenum alloys are a good temperature withstand. A second one-titanium alloy is a best one. Finally concluded by molybdenum alloy is a best suited for design and manufacture in aircraft engines.

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AUTHOR PROFILE

Mr.V.Veeraragavan has received the Master of Engineering from Anna University in 2004. Currently he is working as a Lecturer in Mechanical Engineering, Eritrea Institute of Technology, Ministry of

Education, Eritrea. He has blended his wide experience of 12 years in teaching and research in the field of Mechanical Engineering. He has published a number of international journal papers. His areas of research interest include Heat and Mass Transfer, I.C.Engines and Power Plant Engineering.