scholarly journals Experimental Refinement of Technologies for Environmental Update of Gas Turbine Units Applied to Electrogenerator Driving

1996 ◽  
Author(s):  
A. V. Soudarev ◽  
E. D. Vinogradov ◽  
Ju. I. Zakharov
Keyword(s):  
Gas Turbine ◽  
Maximum Temperature ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Temperature Zone ◽  
Adaptability To Manufacture ◽  
Reduction Of Nox ◽  
Engine Components ◽  
Short Time

The results of experimental elaboration of engineering approaches relating to environmental update of combustors for the GTK-10 10 MW, GTG-1500 1.5 MW and GT-100 100 MW gas turbine engines are presented. The combustor update was carried out by a technique of directed dosed air blow into the maximum temperature zone with in the fire space. The advantages of the technique are as follows: • feasibility of reduction of Nox concentration in waste gases to 50 ppm; • simplicity and adaptability to manufacture of the structure; • no need in changing the design of the engine components and systems; • short-time outage of the unit at update.

scholarly journals Experience With the TF40B Engine in the LCAC Fleet

1992 ◽  
Author(s):  
Edward M. House
Keyword(s):  
Gas Turbine ◽  
Hot Corrosion ◽  
Compressor Blade ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Improvement Program ◽  
Air Cushion ◽  
Engine Components ◽  
Carbon Erosion ◽  
The U.S

Four Textron Lycoming TF40B marine gas turbine engines are used to power the U.S. Navy’s Landing Craft Air Cushion (LCAC) vehicle. This is the first hovercraft of this configuration to be put in service for the Navy as a landing craft. The TF40B has experienced compressor blade pitting, carbon erosion of the first turbine blade and hot corrosion of the hot section. Many of these problems were reduced by changing the maintenance and operation of the LCAC. A Component Improvement Program (CIP) is currently investigating compressor and hot section coatings better suited for operation in a harsh marine environment. This program will also improve the performance of some engine components such as the bleed manifold and bearing seals.

Development and Investigation of Ceramic Parts for Gas-Turbine Engines

1997 ◽  
Author(s):  
Youry A. Nozhnitsky ◽  
Youlia A. Fedina ◽  
Anatoly D. Rekin ◽  
Nickolai I. Petrov
Keyword(s):  
Gas Turbine ◽  
Ceramic Materials ◽  
Mechanical Tests ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Metallic Materials ◽  
Turbine Engine ◽  
Protective Medium ◽  
Gas Generators ◽  
Engine Components

For years of time there have been conducted the investigations of gas-turbine engine parts made of carbon-carbon and ceramic materials. This paper presents mainly the results of works done to create engine components of ceramic materials. There are given the investigation results on development of equipment and methods intended for use in determining the characteristics of heat-resistant non-metallic materials under ultra high temperature conditions. The unique tooling is developed to be used for conducting mechanical tests in different conditions (vacuum, protective medium, air) at temperatures up to 2200°C. There are considered three possible fields of application of ceramic materials, that are, turbine (1), combustion chamber and other stator components operating at high temperatures (2), bearings (3). Different ceramic elements are designed and manufactured, their structural strength is investigated in the laboratory faculties and also as part of engine gas generators.

A Probabilistic Framework for Risk Prediction of Gas Turbine Engine Components With Inherent or Induced Material Anomalies

2005 ◽  
Author(s):  
Michael P. Enright ◽  
R. Craig McClung ◽  
Luc Huyse
Keyword(s):  
Risk Assessment ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Turbine Engines ◽  
Manufacturing Processes ◽  
Gas Turbine Engines ◽  
Probabilistic Framework ◽  
Turbine Engine ◽  
Risk Of Fracture ◽  
Engine Components

Rare anomalies may be introduced during the metallurgical or manufacturing processes that may lead to uncontained failures of aircraft gas turbine engines. The risk of fracture associated with these anomalies can be quantified using a probabilistic fracture mechanics approach. In this paper, a general probabilistic framework is presented for risk assessment of gas turbine engine components subjected to either inherent or induced material anomalies. A summary of efficient computational methods that are applicable to this problem is also provided.

scholarly journals The Viscosity Testing on the Blending of HSD with PPO for Eligibility Criteria of Gas Turbine Fuel as the Renewable Energy Solution

KnE Energy ◽  
2015 ◽  
Vol 2 (2) ◽  
pp. 176
Author(s):  
Tedy Harsanto ◽  
Feti Eka Rahayu
Keyword(s):  
Renewable Energy ◽  
Gas Turbine ◽  
Vegetable Oils ◽  
Palm Oil ◽  
Energy Solution ◽  
Maximum Temperature ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Eligibility Criteria ◽  
Temperature Range

<p>The viscosity of vegetable oils palm oil in particular olein is 18 times higher than the viscosity of HSD. Whereas, the viscosity is allowable for the gas turbine engines which is around 0 to 10 CSt at the maximum temperature of 50 ˚C or when converted to the dynamic viscocity of about 0.78 to 780 mPa.s. In order to meet the gas turbine criteria, so that done the blending between the samples of HSD with PPO and then heated. From the blending of 95 % HSD – 5 % PPO at the temperature range of 30˚ - 35 ˚C were obtained the viscocity value with an average of 3,43 mPas. That results show that the viscosity value of the blending between HSD with PPO still meets the standards of eligibility as a gas turbine fuel. </p><p><strong>Keywords</strong>: Gas turbine; HSD; PPO; temperature; viscosity. <br /><br /></p>

Turbotest: A Computer Program for Rig Test Analysis of Arbitrary Gas Turbine Engines

1984 ◽  
Author(s):  
J. R. Palmer ◽  
Yong-Gen Gu
Keyword(s):  
Gas Turbine ◽  
Test Data ◽  
Hydrocarbon Fuel ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Test Analysis ◽  
Turbine Engine ◽  
Wide Range ◽  
Design Values ◽  
Engine Components

This paper presents a computer model called ‘TURBOTEST’ which is applicable both to analysis of gas turbine engine rig tests and to simulation of engine steady-state performance. As with the earlier ‘TURBOFLEXI’ model a wide range of gas turbine engines can be simulated, using any kind of hydrocarbon fuel, and allowing for chemical dissociation of the gas, and for the effect of air humidity. In addition, however, for the particular requirements of rig test analysis, the following new features have been developed and incorporate:- (a) It can carry out rig test analysis for a wide range of gas turbine engines if all the necessary test data are presented. (b) If the test data is incomplete, a computer simulation of the engine can be used to complete the analysis. (c) Performance deterioration of engine components can be detected by comparing the results of a test analysis and of a parallel simulation using stored characteristics of engine components in the “as new” condition. The program has been tested on simulated test data generated by engine models such as a turbojet and a turbofan. The results show it has close and repeatable agreement with design values. Further tests of the model have been carried out by applying it to the actual engine rig test data.

Multiharmonic Analysis of Nonlinear Whole Engine Dynamics With Bladed Disc-Casing Rubbing Contacts

2012 ◽  
Author(s):  
E. P. Petrov
Keyword(s):  
Gas Turbine ◽  
Frequency Domain Analysis ◽  
Forced Response ◽  
Contact Forces ◽  
Turbine Engines ◽  
Test Cases ◽  
Gas Turbine Engines ◽  
Interface Elements ◽  
Friction Forces ◽  
Engine Components

A method has been developed for frequency domain analysis of steady state forced response in gas turbine engines in the presence of rubbing and snubbing contacts between bladed discs and casing and between other rotor and stator engine components. The multiharmonic contact interface elements have been derived for modelling the nonlinear contact interactions: (i) at bearings and (ii) bladed disc-casing rubbing contacts with using flexible models for rotor and stator structures. The elements allow for the asymmetry of the casing, the discrete blade contacts with casing, individual blade-casing gap values, nonlinear dependency of the contact forces on rotor-stator incursion and friction forces, intermittent contacts between blades and the casing. High accuracy and computational efficiency of the methods and models developed has been demonstrated on a set of test cases and on an example of analysis of a realistic gas turbine structure.

The Application of Ceramics to the Small Gas Turbine

1970 ◽  
Author(s):  
A. F. McLean
Keyword(s):  
Gas Turbine ◽  
Lower Cost ◽  
Ceramic Materials ◽  
Turbine Engines ◽  
Inlet Temperature ◽  
Gas Turbine Engines ◽  
Turbine Inlet Temperature ◽  
Turbine Engine ◽  
Engine Components ◽  
Processing Techniques

This paper reviews the limitations today’s superalloys exercise on the realization of the potential of the gas turbine engine. Ceramic materials are suggested as a means of achieving lower cost and higher turbine inlet temperature in small gas turbine engines. The paper serves to introduce ceramic materials and processing techniques and identifies silicon nitride, silicon carbide and lithium-alumina-silicate as promising materials for high temperature turbine engine components.

Power Turbine Vane Ring (PT6 Engine) Repair Development

1986 ◽  
Author(s):  
N. Sourial
Keyword(s):  
Gas Turbine ◽  
High Technology ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Turbine Engine ◽  
New Methods ◽  
Power Turbine ◽  
Turbine Vane ◽  
Engine Components ◽  
Repair Techniques

Today’s high technology gas turbine engines incorporate the world’s most exotic alloys and are built to some of the most precise dimensional tolerances encountered in any industry. The constant drive for increased performance while substantially reducing fuel consumption and weight has pushed engine components and their designers to limits never before realized. To achieve these limits new methods and materials have evolved; not exclusively in the production of the engines but also in the repair and maintenance of them. The typical problems encountered in repair and maintenance are numerous and varied as are their solutions. This paper, however, will concentrate on one in particular and that is the typical damage encountered on a first stage power turbine vane ring and the technology employed to repair such damage. The vane ring was chosen because it is representative of a common problem encountered by all gas turbine engine manufacturers and simultaneously involves some of the most up to date repair techniques to restore it.

scholarly journals THE FORMATION OF HIGH TEMPERATURE MINERALS FROM AN EVAPORITE-RICH DUST IN GAS TURBINE ENGINE INGESTION TESTS

2021 ◽  
pp. 1-11
Author(s):  
Jacob Elms ◽  
Alison Pawley ◽  
Nicholas Bojdo ◽  
Merren Jones ◽  
Rory J. Clarkson
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Previous Analysis ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Complete Understanding ◽  
Turbine Engine ◽  
Mineral Assemblages ◽  
Mineral Dusts ◽  
Engine Components

Abstract The ingestion of multi-mineral dusts by gas turbine engines during routine operations is a significant problem for engine manufacturers because of the damage caused to engine components and their protective thermal barrier coatings. A complete understanding of the reactions forming these deposits is limited by a lack of knowledge of compositions of ingested dusts and unknown engine conditions. Past engine tests have used standardised test dusts that do not resemble the composition of the background dust in the operating regions. A new evaporite-rich test dust was developed and used in a full engine ingestion test, designed to simulate operation in regions with evaporite-rich geology, such as Doha or Dubai. Analysis of the engine deposits showed that mineral fractionation was present in the cooler, upstream sections of the engine. In the hotter, downstream sections, deposits contained new, high temperature phases formed by reaction of minerals in the test dust. The mineral assemblages in these deposits are similar to those found from previous analysis of service returns. Segregation of anhydrite from other high temperature phases in a deposit sample taken from a High Pressure Turbine blade suggests a relationship between temperature and sulfur content. This study highlights the potential for manipulating deposit chemistry to mitigate the damage caused in the downstream sections of gas turbine engines. The results of this study also suggest that the concentration of ingested dust in the inlet air may not be a significant contributing factor to deposit chemistry.

scholarly journals Embedded Temperature Sensor Evaluations for Turbomachinery Component Health Monitoring

Energies ◽  
2021 ◽  
Vol 14 (4) ◽  
pp. 852
Author(s):  
Muthuvel Murugan ◽  
Michael Walock ◽  
Anindya Ghoshal ◽  
Robert Knapp ◽  
Roger Caesley
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Ceramic Matrix Composites ◽  
Sensor Technology ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Foreign Technology ◽  
Embedded Sensing ◽  
Engine Components ◽  
Temperature Responses

Current rotorcraft gas turbine engines typically use titanium alloys and steel for the compressor section and single-crystal nickel superalloys for the hot-section turbine stator vanes and rotor blades. However, these material selections are rapidly changing due to increased requirements of power-density and efficiency. Future U.S. Army gas turbine engines will be using ceramic matrix composites for many high temperature engine components due to their low density and improved durability in high temperature environments. The gas turbine industry is also actively developing adaptive concept technologies for production and assembly of modular gas turbine engine components with integrated sensing. In order to actively monitor engine components for extended seamless operation and improved reliability, it is essential to have intelligent embedded sensing to monitor the health of critical components in engines. Under this U.S. Army Foreign Technology Assessment Support (FTAS) program funded research project, embedded fiber-optic temperature sensors from U.K.-based company, Epsilon Optics Ltd (Fordingbridge, UK)., were experimentally evaluated to measure temperature responses on typical turbomachinery component material coupons. The temperature responses from this foreign technology sensor were assessed using a thermomechanical fatigue tester with a built-in furnace to conduct thermal cycling durability experiments. The experimental results obtained from the durability performance of this embedded fiber Bragg sensor are reported in this paper. This sensor technology, upon maturation to higher TRL (technology readiness level), can greatly reduce the lifecycle cost of future U.S. Army gas turbine engines.

Sign in / Sign up

Export Citation Format

Share Document