Finite Element Approach for Failure Analysis of a Gas Turbine Blade
- PDF / 2,098,550 Bytes
- 6 Pages / 595.276 x 790.866 pts Page_size
- 75 Downloads / 216 Views
TECHNICAL ARTICLE—PEER-REVIEWED
Finite Element Approach for Failure Analysis of a Gas Turbine Blade P. Balachandra Shetty . R. K. Mishra . S. S. Prithvi . R. Lohith . B. M. Karthik . D. M. Lohith
Submitted: 30 June 2018 / Published online: 20 July 2018 ASM International 2018
Abstract In the present work, a case study on the gas turbine blade is undertaken for failure analysis through finite element approach. The analysis is carried out through simulation and validated analytically and experimentally. The challenging point in the failure analysis of turbine blade is to obtain the exact morphology of the turbine blade for computation. It is accomplished by extracting the real operational turbine blade of an engine with its solid model through finite element analysis for thermo-mechanical loads. Extensive service exploitation of the engine and adverse operational conditions have made the annular gap between the blade tips and turbine casing distorted and nonuniform tip clearance. The maximum elongation of the turbine blade was found to exceed the minimum tip clearance in the rotor causing rubbing of the blade in the casing. Rubbing of the blade has been finally found to be responsible for the failure of the cantilever blade. Keywords Gas turbine Turbine blade Failure analysis Tip clearance
Introduction Premature failure of gas turbine blades is often noticed due to their operation at extreme conditions of pressure, thermal load and inertia loads. Turbine blades generally fail P. Balachandra Shetty S. S. Prithvi R. Lohith B. M. Karthik D. M. Lohith Nitte Meenakshi Institute of Technology, Bangalore, India R. K. Mishra (&) Centre for Military Airworthiness and Certification, Bangalore, India e-mail: [email protected]
123
because of creep, oxidation, low-cycle fatigue (LCF) and high-cycle fatigue (HCF). In the present work, the turbine blade of a gas turbine engine has been analyzed through finite element method using commercially available software for the mechanical and structural integrity. The researchers worldwide have been working extensively to analyze turbine blade failures so that corrective measures can be incorporated at design stage, in manufacturing line and during operation to prevent catastrophic situations. Kolagari et al. [1] in their paper have outlined failure analysis of gas turbine blades of nickel-based superalloy. Gamannossi et al. [2] in their paper have interpreted that the progressive development in terms of gas turbine materials as well as blade cooling systems would direct to continuous growth in the turbine inlet temperature and the overall pressure ratio to achieve higher thermal efficiency and power output. Giuntini et al. [3] have illustrated some preliminary results from the test of the procedure applied to a simplified model representative of real engine geometry under transient conditions. Vincenzo cuffaro et al. [4] have studied the behavior of the turbine blades at very high temperature varying over time, high thermal gradients, creep-related phenomenon, mech
Data Loading...
