Your Selections

Gas turbines
Show Only

Collections

File Formats

Content Types

Dates

Sectors

Topics

Authors

Publishers

Affiliations

Committees

Events

Magazine

Series

   This content is not included in your SAE MOBILUS subscription, or you are not logged in.
new

Assessment of Numerical Cold Flow Testing of Gas Turbine Combustor through an Integrated Approach Using Rapid Prototyping and Water Tunnel

Indian Institute of Technology Madras-Ssheshan Pugazhendhi
SRM Institute of Science and Technology-Sundararaj Senthilkumar
  • Technical Paper
  • 2019-28-0051
Published 2019-10-11 by SAE International in United States
In the present work, it is aimed at developing an integrated approach for combustor modeling involving rapid prototyping and water tunnel testing to assess the cold flow numerical simulations; the physical model will be subjected to cold flow visualization and parametric studies and CFD analysis to demonstrate its capability for undergoing rigorous cold flow testing. A straight through annular combustors is chosen for the present study because of it has low pressure drop, less weight and used widely in modern day aviation engines.Numerical Analysis has been performed using ANSYS-FLUENT. Three dimensional RANS equations are solved using k-ɛ model for the Reynolds numbers ranging from 0.64 x 105-1.5 x 105 based on the annulus diameter. Post processing the results is done in terms of jet penetration, formation of recirculation zone, effective mixing, flow split and pressure drop for different cases. Physical combustor models are fabricated using Rapid prototyping with Poly Lactic Acid material and approximated 2D combustor model is used for capturing important flow patterns using high speed camera in 2D water tunnel, and for pressure…
This content contains downloadable datasets
Annotation ability available
   This content is not included in your SAE MOBILUS subscription, or you are not logged in.
new

Parameter Optimization during Minimum Quantity Lubrication Turning of Inconel 625 Alloy with CUO, Al2O3 and CNT Nanoparticles Dispersed Vegetable-Oil-Based Cutting Fluid

Vellore Institute of Technology-Venkatesan Kannan, Devendiran Sundararajan
  • Technical Paper
  • 2019-28-0061
Published 2019-10-11 by SAE International in United States
Inconel 625, nickel based alloy, is found in gas turbine blades, seals, rings, shafts, and turbine disks. On the other hand, the manufacturing of this alloy is challenging, mainly when machining processes are used due to excellent mechanical properties. Application of nanofluids in minimum quantity lubrication (MQL) shows gaining importance in the machining process, which is economical and eco-friendly. The principal objective of this investigational work is to study the influence of three types of nanofluids in the MQL turning of Inconel 625 nickel based alloys. The used nanofluids are multi-walled carbon nanotubes (CNT), alumina (Al2O3) and copper oxide (CUO) dispersed in vegetable oil. Taguchi-based L27 orthogonal array is used for the experimental design. The parameter optimization of design variables over response is carried out by the use of Taguchi-based derringer's desirability function. The design variables are machining parameters (speed, feed), nanofluids (Al2O3, CNT, CUO), and three different weight percentage (0.1, 0.25, and 0.5 wt. %). The results showed that minimum values of surface roughness could be achieved at 0.10 wt. % of nanoparticles, CNT…
This content contains downloadable datasets
Annotation ability available
   This content is not included in your SAE MOBILUS subscription, or you are not logged in.
new

Advanced Exergy Analysis of an Air Craft Gas Turbine Engine at Different Power Loading Operations

GIFT, Bhubaneshwar-Alok Kumar Mohapatra
VIT Universtity Vellore-Tapano Hotta
Published 2019-09-16 by SAE International in United States
The innovations in aircraft propulsion have been identified as the key parameter towards the progress in transportation. Continuous advancement in the performance and efficiency of propulsion has enabled aircraft to travel over larger distances with higher speed. Aviation is also responsible for approximately 2% of total greenhouse gas emission and is expected to grow around 3% by 2050. The present article aims to use the exergetic analysis of a turboprop engine which should be helpful in designing of such engines and also helps these engine users to regulate and select the operation modes. A gas turbine with film air cooling of turbine blades has been proposed to be the turboprop engine. The engine is analyzed on exergy point of view at different power loading operation modes and the performance is studied. Selected exergetic measures under consideration are Exergy Efficiency, Fuel Exergy Depletion Ratio, Relative Exergy Consumption Ratio, Exergetic Improvement potential and Productivity Lack ratio. The total fuel exergy depletion ratio of the turboprop engine is estimated to be around 64.7 % at 100% loading. Also,…
This content contains downloadable datasets
Annotation ability available
   This content is not included in your SAE MOBILUS subscription, or you are not logged in.
new

A Practical Recuperated Split Cycle Engine for Low Emissions and High Efficiency

Dolphin N2 Ltd-Nicholas Owen, Fabrizio Treccarichi
Hiflux Limited-David Barnes, Tanzi Besant
Published 2019-09-09 by SAE International in United States
The Recuperated Split Cycle Engine is a new type of ICE, offering a step change in efficiency and tailpipe emissions. It targets the heavy duty, long-haul sector (trucks, off-highway, rail, shipping), where electrification is most challenging, and distributed generation, where capacity is required to support rising electrification. The engine separates cold (induction, compression) and hot (combustion, expansion) parts of the cycle; waste exhaust heat is recovered between them via a recuperator, as in a recuperated gas turbine. Recent research presented at this conference [1] shows that the sonic airflows seen in the induction event give rise to extraordinary fuel mixing and clean, cool combustion, with potential for after-treated emission levels between SULEV and zero-impact (either unmeasurable or below ambient). Recuperation and thermal insulation of the hot cylinder (both feasible within the capability of common materials) also enable high thermal efficiency, with a flatter efficiency map than a conventional ICE. Combining the two attributes, and introducing sustainable fuels, places this readily manufactured, affordable technology on a par with battery-electric and fuel cell propulsion. Results from simulation…
This content contains downloadable datasets
Annotation ability available

Microturbine Propulsion for UAVs

  • Magazine Article
  • TBMG-34863
Published 2019-08-01 by Tech Briefs Media Group in United States

Seventy years ago, military aviation moved from reciprocating engines to vastly more reliable turbo jets and turboprops. Shortly after, the commercial air transport industry followed suit, enabling modern air transport. Today, virtually all large aircraft rely on turbine propulsion, yet small aircraft, both manned and unmanned, have not exploited the advantages of turbines for propulsion.

   This content is not included in your SAE MOBILUS subscription, or you are not logged in.

Test Cell Analytical Thrust Correction

EG-1E Gas Turbine Test Facilities and Equipment
  • Aerospace Standard
  • AIR5436A
  • Current
Published 2019-07-02 by SAE International in United States
This document describes a method to correct engine thrust, measured in an indoor test cell, for the aerodynamic effects caused by the secondary airflow induced in the test cell by the engine operating in an enclosed environment in close proximity to an exhaust duct. While it is not recommended to be used to replace test cell correlation, it does provide a means to verify an existing thrust correlation factor.
This content contains downloadable datasets
Annotation ability available
   This content is not included in your SAE MOBILUS subscription, or you are not logged in.

Experimental Study and Analysis of Ice Crystal Accretion on a Gas Turbine Compressor Stator Vane

Rolls-Royce Plc-Geoffrey Jones, Benjamin Collier, Alasdair Reed
University of Oxford-Alexander Bucknell, Matthew McGilvray, David Gillespie, Peter Forsyth, Hassan Saad Ifti
Published 2019-06-10 by SAE International in United States
A significant number of historical engine powerloss events have recently been attributed to ingestion of high altitude ice crystals, prompting regulators to expand engine certification envelopes to incorporate ‘ice crystal icing’ conditions. There has been a resulting effort by OEMs and academia to develop analytical and semi-empirical models for the phenomenon, partly through use of rig testing. The current study presents results and analysis of experiments conducted in the National Research Council’s Research Altitude Test Facility (RATFac). The experiments used a simplified compressor stator vane test article, designed to produce data to build semi-empirical models and validate an existing ice crystal icing code. Accretion growth rates, extracted from backlit shadowgraphy, are presented as a function of test condition, and the algorithm of a new image processing technique using Canny filtering is discussed. Wet bulb temperature, Mach number, particle size and test article angle of attack were systematically varied. In line with previous experiments, the accretion growth rate was observed to be strongly dependent upon bulk particle melt ratio, with a peak growth rate at approximately…
This content contains downloadable datasets
Annotation ability available
   This content is not included in your SAE MOBILUS subscription, or you are not logged in.

Icing Test and Measurement Capabilities of the NRC’s Gas Turbine Laboratory

National Research Council Canada-Jennifer Chalmers, Craig Davison, James MacLeod, Martin Neuteboom, Dan Fuleki
Published 2019-06-10 by SAE International in United States
The National Research Council’s Gas Turbine Laboratory provides industry leading icing facilities that allow manufacturers to develop, validate and certify new products for flight in adverse conditions. This paper shows how NRC measurement techniques are used across the facilities, and presents a literature-review of recently developed capabilities. The overview includes new details on some facilities, and future capabilities that are in development or planned for the near future.Methods developed at the NRC for characterizing inclement conditions are discussed and include the Isokinetic Probe, Particle Shadow Velocimetry, the Particle Detection Probe, and a size-binned real-time thermodynamic evaporation model. These are used to deliver accurate icing water content in facilities like the sea-level ice crystal generator, the Rotating Icing Rig, the Research Altitude Testing Facility, and liquid water test facilities in Ottawa and in Thompson, Manitoba at the Global Aerospace Centre for Icing and Environmental Research (GLACIER).
This content contains downloadable datasets
Annotation ability available
   This content is not included in your SAE MOBILUS subscription, or you are not logged in.

Balancing Machines, Dynamic, Ball Type Slave Bearings for Rotor Support

EG-1A Balancing Committee
  • Aerospace Standard
  • ARP1202B
  • Current
Published 2019-04-25 by SAE International in United States
This ARP specifies both the nominal dimensions and the tolerances for a series of ball bearings with semifinished inside diameters which are suitable for supporting gas turbine rotating components in dynamic balancing machines.
This content contains downloadable datasets
Annotation ability available
   This content is not included in your SAE MOBILUS subscription, or you are not logged in.

SI Engine Combustion and Knock Modelling Using Detailed Fuel Surrogate Models and Tabulated Chemistry

AVL Dacolt BV-Dmitry Goryntsev, Ferry Tap
AVL List GmbH-Mijo Tvrdojevic, Peter Priesching
Published 2019-04-02 by SAE International in United States
In the context of today’s and future legislative requirements for NOx and soot particle emissions as well as today’s market trends for further efficiency gains in gasoline engines, computational fluid dynamics (CFD) models need to further improve their intrinsic predictive capability to fulfill OEM needs towards the future. Improving fuel chemistry modelling, knock predictions and the modelling of the interaction between the chemistry and turbulent flow are three key challenges to improve the predictivity of CFD simulations of Spark-Ignited (SI) engines. The Flamelet Generated Manifold (FGM) combustion modelling approach addresses these challenges. By using chemistry pre-tabulation technologies, today’s most detailed fuel chemistry models can be included in the CFD simulation. This allows a much more refined description of auto-ignition delays for knock as well as radical concentrations which feed into emission models, at comparable or even reduced overall CFD run-time. The FGM model has a high level of intrinsic predictive capability, as already demonstrated for many academic cases as well as for industrial burners, gas turbines and diesel engines. The application to gasoline engines has…
This content contains downloadable datasets
Annotation ability available