HIGH STRENGTH STRUCTURAL STEELS FOR GAS-TURBINE ENGINE SHAFTS (review)

2021 ◽  
pp. 3-12
Author(s):  
V.I. Gromov ◽  
◽  
N.A. Yakusheva ◽  
A.V. Vostrikov ◽  
N.N. Cherkashneva ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Mechanical Characteristics ◽  
High Strength ◽  
Gas Turbine Engine ◽  
Structural Steels ◽  
Motor Shaft ◽  
Turbine Engine ◽  
Term Operation ◽  
Loaded Part

The motor shaft of a gas turbine engine, being a highly loaded part of a particularly critical purpose, has increased requirements for maintaining the level of properties during long-term operation, ensuring the structural strength of the product. An increase in the resource and durability of the product is achieved due to the development of new materials that surpass the used domestic and foreign analogues in their mechanical characteristics. FSUE «VIAM» has deve-loped high-strength structural steels with enhanced characteristics of strength, toughness, durability and heat resistance.

Paper 7: Advanced Nickel-Chromium Base Alloys

1965 ◽  
Vol 180 (4) ◽  
pp. 160-171
Author(s):  
C. H. White ◽  
J. Heslop
Keyword(s):  
High Temperature ◽  
Binary System ◽  
Gas Turbine ◽  
Elevated Temperatures ◽  
High Strength ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Nickel Chromium ◽  
Chromium Alloys ◽  
Resistance To Oxidation

Nickel-chromium alloys have been in use since early in this century for high temperature applications because of their resistance to oxidation. Since the advent of the gas-turbine engine, more complex alloys capable of maintaining high strength at elevated temperatures have been developed from the simple binary system. These complex alloys were initially mainly strengthened by the precipitation of the Ni3(Ti, Al) phase but more recent alloys have been further strengthened by additions of cobalt, tungsten, molybdenum, niobium, and tantalum. The properties and applications of these alloys are discussed.

scholarly journals Data Analytics for Performance Monitoring of Gas Turbine Engine

2018 ◽  
Vol 10 (1) ◽  
Author(s):  
Yuan Liu ◽  
Avisekh Banerjee ◽  
Thambirajah Ravichandran ◽  
Amar Kumar ◽  
Glenn Heppler
Keyword(s):  
Gas Turbine ◽  
Performance Monitoring ◽  
Gas Turbine Engine ◽  
Short Term ◽  
Turbine Engine ◽  
Free Data ◽  
Performance Deterioration ◽  
Long Term Performance ◽  
Term Performance

Performance analysis of a low power rating and partially loaded industrial gas turbine engine (GTE) was carried out by using a model-free data analytic approach. By adopting an efficient input selection method, several performance indices (PI) are proposed to quantify the performance of the GTE. These indices are extracted using engine operating data related to power output and parameters related to fuel consumption, and validated with engine performance monitoring measurements for a three year period corresponding to one time between overhaul intervals. The dependency of the PIs on ambient temperature has been studied by using linear and polynomial fitting curves. Then novel methods are introduced for analysis of short-term and long-term performance deterioration arising from compressor fouling and structural degradation respectively. The results have clearly shown the ability of the proposed PIs to detect short-term compressor fouling as well as long-term performance deterioration, which is directly relevant to the Prognostics and Health Management of gas turbine engine.

Rig and Gas Turbine Engine Testing of MI-CMC Combustor and Shroud Components

2001 ◽  
Author(s):  
Gregory Corman ◽  
Anthony Dean ◽  
Stephen Brabetz ◽  
Keith McManus ◽  
Milivoj Brun ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Ceramic Matrix Composites ◽  
Gas Turbine Engine ◽  
Matrix Composites ◽  
Turbine Engine ◽  
Single Piece ◽  
Engine Testing ◽  
Engine Components ◽  
Industrial Gas Turbine

GE is continuing work on the development of Melt-Infiltrated Ceramic Matrix Composites (MI-CMC) for use in industrial gas turbine engine components. Long-term environmental degradation of test samples under realistic engine conditions is being determined using a unique high-pressure combustion rig apparatus. Rig testing is also being used to evaluate an F-class 1st stage shroud system incorporating an MI-CMC inner shroud component. While large, advanced engines, such as the F and H classes, offer the greatest benefits for using MI-CMC components, initial engine tests have been done using a GE-2 (2MW) machine to reduce costs and risk. Long term (1000 hours) engine testing results for single piece GE-2 shrouds are also described.

Statistical Analysis of Casting Defects in Microstructure for Understanding the Effect on Fatigue Property of 17-4PH Stainless Steel

2006 ◽  
Vol 321-323 ◽  
pp. 1503-1506 ◽  
Author(s):  
Jong Yup Kim ◽  
Joon Hyun Lee ◽  
Seung Hoon Nahm
Keyword(s):  
Stainless Steel ◽  
Statistical Analysis ◽  
Gas Turbine ◽  
Fatigue Property ◽  
High Strength ◽  
Casting Process ◽  
Gas Turbine Engine ◽  
Quality Level ◽  
Casting Defects ◽  
Turbine Engine

High strength materials have been used for critical components in order to ensure the reliability of aircraft gas turbine engine. But it usually costs high to maintain their premium quality. Therefore, the optimum quality level of materials should be defined under operating condition by material property estimation technique in order to meet the requirement of reliability and economical efficiency. Most cast rotating parts of gas turbine engine have casting defects caused during the casting process. The casting defects less than certain acceptable limit can be permissible for usage. So, it is very important to understand material defect shape and distribution, and its effect on mechanical properties exactly. In this study, 17-4PH stainless steel specimens with variable internal casting defects were prepared to investigate the fatigue property characteristics. The defect fraction and condition were estimated in microstructure by statistical analysis. The correlation between estimated defect condition and fatigue property was discussed.

scholarly journals Experience in using anisotropic properties of composites in engineering the compressor impeller of a small-size gas turbine engine

2020 ◽  
Vol 329 ◽  
pp. 03029
Author(s):  
L. A. Martynyuk ◽  
L. V. Bykov ◽  
A. D. Ezhov ◽  
P. I. Talalaeva ◽  
D. V. Afanasiev
Keyword(s):  
Composite Materials ◽  
Gas Turbine ◽  
Centrifugal Compressor ◽  
High Strength ◽  
Gas Turbine Engine ◽  
Rocket Engines ◽  
Turbine Engine ◽  
Anisotropy Of Properties ◽  
Reinforcing Fibers ◽  
Compressor Impeller

The use of composite materials in modern aircraft and rocket engines is one of the most promising areas. Low density and high strength characteristics of composite materials are crucial when choosing a material for small-sized compressors. The main ability to bear the load of the composite material is provided by the reinforcing fibers of the filler. The greater the percentage of filler fibers has a particular orientation, the higher the strength and rigidity of the product in this direction. If the part is loaded with forces applied primarily in one or two directions, it makes sense to create a material with anisotropy of properties that will exactly match the applied loads. For example, the disk and blades of a centrifugal compressor operate under the action of centrifugal force and gas pressure. In this case, to manufacture a centrifugal compressor impeller from composite materials, it is only necessary to redistribute the fibers in the part space in such a way as to create an optimal anisotropy of properties. This article describes the procedure for selecting the optimal orientation of reinforcing fibers in the impeller of a centrifugal compressor of a small gas turbine engine.

Validation of ATI 20-25+Nb™ Alloy at 50,000 Hours in the Recuperator of a Gas Turbine Engine

2012 ◽  
Author(s):  
M. D. Bender ◽  
J. M. Rakowski ◽  
M. D. Lipschutz
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Field Test ◽  
Gas Turbine Engine ◽  
Test Program ◽  
Temperature Oxidation ◽  
Turbine Engine ◽  
Alloy 625 ◽  
Turbine Exhaust

A field test program to validate high temperature oxidation resistance of the ATI 20-25+Nb™ alloy in a Solar Turbines Incorporated Mercury™ 50 gas turbine engine has exceeded 50,000 operating hours. A primary goal of this program is to assess the effect of the actual recuperator operating environment on high temperature degradation of primary surface recuperator (PSR) materials. As PSRs are generally fabricated from thin foil materials, excessive degradation can cause perforation, leading to failure of components. To avoid such problems, PSRs are generally fabricated from nickel-base superalloys or highly-alloyed austenitic stainless steels. Previously, ATI 20-25+Nb (UNS S35140) stainless steel was developed and experimentally shown to have excellent creep resistance and good environmental resistance for a PSR application. This field test program evaluates the long-term performance of this alloy in situ in turbine exhaust and compares it with the more highly alloyed Ni-based 625 superalloy. Sub-size air cell samples of alloy 625 and ATI 20-25+Nb alloy exposed for 50,000 hours (running time) in turbine exhaust were removed and tested for materials characterization. Analysis showed that both alloy 625 and ATI 20-25+Nb alloy exhibit excellent long-term resistance to environmental degradation, even after service exposure equivalent to over 5.5 years.

Long-Term Durability and Rigidity of Structurally Heterogeneous Gas Turbine Engine Blades

2020 ◽  
Vol 63 (2) ◽  
pp. 197-204
Author(s):  
A. V. Mishchenko ◽  
Yu. V. Nemirovskii
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Turbine Engine

Comparison of Ni-Based 625 Alloy and ATI 20-25+Nb™ Stainless Steel Foils After Long-Term Exposure to Gas Turbine Engine Exhaust

2014 ◽  
Author(s):  
M. D. Bender ◽  
R. C. Klug
Keyword(s):  
Stainless Steel ◽  
High Temperature ◽  
Gas Turbine ◽  
Field Test ◽  
Gas Turbine Engine ◽  
Test Program ◽  
Temperature Oxidation ◽  
Turbine Engine ◽  
Turbine Exhaust

A field test program to validate the high temperature oxidation resistance of the ATI 20-25+Nb™ alloy in a Solar Turbines Incorporated Mercury™ 50 gas turbine engine has exceeded 66,000 operating hours. The primary goal of this program is to assess the effect of the actual recuperator operating environment on the high temperature degradation of primary surface recuperator (PSR) materials. As PSRs are generally fabricated from thin foil materials, excessive degradation can cause perforation or collapse, leading to decreased performance or failure. To avoid such issues, PSRs are generally fabricated from highly-alloyed austenitic stainless steels or nickel-base superalloys. This field test program evaluates and compares the long-term performance of the iron-based austenitic ATI 20-25+Nb™ stainless steel (UNS S35140) with the more highly alloyed nickel-based 625 alloy (UNS N06625) in an in-situ turbine exhaust environment. Sub-size air cell samples of alloy 625 and ATI 20-25+Nb™ alloy, exposed for 66,000 hours (running time) in turbine exhaust, were removed and tested for materials characterization. Analysis showed that both alloys exhibit excellent long-term resistance to environmental degradation, even after service exposures equivalent to over 7.5 years.

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