scholarly journals Estimation and Mitigation of Unknown Airplane Installation Effects on GPA Diagnostics

Machines ◽  
2022 ◽  
Vol 10 (1) ◽  
pp. 36
Author(s):  
Mikael Stenfelt ◽  
Konstantinos Kyprianidis
Keyword(s):  
Design Process ◽  
Gas Turbines ◽  
Diagnostic System ◽  
Power Extraction ◽  
Installation Effects ◽  
Degradation Pattern ◽  
Shaft Power ◽  
Air Intake ◽  
Intake Pressure ◽  
Diagnostic Framework

In gas turbines used for airplane propulsion, the number of sensors are kept at a minimum for accurate control and safe operation. Additionally, when data are communicated between the airplane main computer and the various subsystems, different systems may have different constraints and requirements regarding what data transmit. Early in the design process, these parameters are relatively easy to change, compared to a mature product. If the gas turbine diagnostic system is not considered early in the design process, it may lead to diagnostic functions having to operate with reduced amount of data. In this paper, a scenario where the diagnostic function cannot obtain airplane installation effects is considered. The installation effects in question is air intake pressure loss (pressure recovery), bleed flow and shaft power extraction. A framework is presented where the unknown installation effects are estimated based on available data through surrogate models, which is incorporated into the diagnostic framework. The method has been evaluated for a low-bypass turbofan with two different sensor suites. It has also been evaluated for two different diagnostic schemes, both determined and underdetermined. Results show that, compared to assuming a best-guess constant-bleed and shaft power, the proposed method reduce the RMS in health parameter estimation from 26% up to 80% for the selected health parameters. At the same time, the proposed method show the same degradation pattern as if the installation effects were known.

scholarly journals Fugitive Methane Emission Reduction Using Gas Turbines

1998 ◽  
Author(s):  
Todd Parker
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Cost Effective ◽  
Process Gas ◽  
Natural Gas Transmission ◽  
Air Intake ◽  
Lean Fuel ◽  
Gas Seals ◽  
Turbo Compressor ◽  
Many Sources

Natural gas transmission systems have many sources of fugitive methane emissions that have been difficult to eliminate. This paper discusses an option for dealing with one such source for operations using turbo-compressor units fitted with dry gas seals. Dry seals rely on a small leakage of process gas to maintain the differential pressure of the process against the atmosphere. The seal leakage ultimately results in waste gas that is emitted to the atmosphere through the primary vent. A simple, cost effective, emission disposal mechanism for this application is to vent the seal gas into the gas turbine’s air intake. Explosion hazards are not created by the resultant ultra-lean fuel/air mixture, and once this mixture reaches the combustion chamber, where sufficient fuel is added to create a flammable mixture, significant oxidation of the seal vent gas is realized. Background of the relevant processes is discussed as well as a review of field test data. Similar applications have been reported [1] for the more generalized purpose of Volatile Organic Compound (VOC) destruction using specialized gas turbine combustor designs. As described herein, existing production gas turbine combustors are quite effective at fugitive methane destruction without specialized combustor designs.

Prediction of the Acoustic Reflection in a Realistic Aeroengine Intake With Three Numerical Methods to Analyze Fan Flutter

2020 ◽  
Author(s):  
Thomas Bontemps ◽  
Stéphane Aubert ◽  
Maxime de Pret
Keyword(s):  
Analytical Model ◽  
Design Process ◽  
Cfd Simulation ◽  
Computational Cost ◽  
Fidelity Level ◽  
Acoustic Reflection ◽  
Acoustic Coupling ◽  
Air Intake ◽  
Operating Points ◽  
Do So

Abstract For a particular range of frequencies, an acoustic coupling between the fan and the air intake can modify fan stability regarding flutter. Previous works have shown that characterizing the reflection on the intake opening might be a crucial element to target operating points for which the risk of acoustic driven flutter is high. To do so, three methodologies are compared in this paper: an aeroelastic CFD simulation, an acoustic potential simulation and an analytical model. Each of them has a different fidelity level and computational cost, what makes their usage more beneficial at some step in the design process. It is shown that results of aeroelastic CFD and acoustic potential simulations are in excellent agreement. Fast acoustic simulations are then a good option in the early design process. The analytical model presents an important error mainly on the phase, and should be adapted before usage.

A Method to Compare Turbine Engine Airstart Times

2007 ◽  
Author(s):  
Wade Casey ◽  
Donald Malloy ◽  
Steve Arnold ◽  
Gregory Shaff ◽  
David Kidman
Keyword(s):  
Analytical Approach ◽  
Simulation Test ◽  
Engine Operation ◽  
Turbofan Engine ◽  
Turbine Engine ◽  
Power Extraction ◽  
Installation Effects ◽  
Fuel Flow ◽  
Starter Motor ◽  
The Difference

Turbine engine airstarts are conducted throughout the aircraft airspeed/altitude envelope in ground-based simulation test facilities and in flight tests to ensure safe and reliable engine operation. Differences in airstart times are attributable to variations in engine turnaround speed (the engine core speed at which the airstart is initiated in spooldown airstarts); combustor lightoff time; installation effects such as customer bleed and power extraction; starter motor torque; fuel flow scheduling; and engine-to-engine variation and degradation. An analytical approach is presented to account for these differences and adjust engine airstart time for a low-bypass, twin-spool, military, turbofan engine. Two examples are presented illustrating the difference in airstart times and the analytical approach used to adjust the start times.

SECONDARY POWER SYSTEM EVALUATIONS FOR ADVANCED AIRCRAFT

1999 ◽  
Vol 23 (1B) ◽  
pp. 117-127
Author(s):  
R. Lykins ◽  
M. Ramalingam ◽  
B. Donovan ◽  
E. Durkin ◽  
J. Beam
Keyword(s):  
Power Systems ◽  
Power System ◽  
Data Transfer ◽  
Engine Performance ◽  
Air Power ◽  
Power Extraction ◽  
Resultant Data ◽  
Shaft Power ◽  
The Impact ◽  
Engine Cycle

A computerized analytical program is being developed to help investigate the impact of power system requirements on aircraft performance. The program has an user interface that operates in MS-EXCEL, linking several subsystems analysis programs for execution and data transfer in the power systems analysis. The program presently includes an encoded propulsion engine cycle code, which allows the inspection of power extraction effects on engine performance. To validate the results of the encoded engine program, a study was conducted to investigate the separate effects of shaft power extraction and pneumatic bleed. The selected engine cycle was that for a standard tactical fighter, with a flight condition of varied altitude (sea level to 40,000 ft) and constant Mach Number (0.9). As expected the resultant data showed that the engine performance was more sensitive to pneumatic bleed than to shaft power extraction. The paper’s efficiency comparisons between shaft power and bleed air power helps indicate the higher efficiency for the power system of a more-electric type aircraft. Present efforts on the analytical interface are to incorporate a fuel thermal management analysis capability.

scholarly journals Combined Gas Turbine and Diesel Generator Cooling Air Intake System

1998 ◽  
Author(s):  
Roger Yee ◽  
Alan Oswald
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Lessons Learned ◽  
Aviation Fuel ◽  
Diesel Generator ◽  
Intake System ◽  
Air Intake ◽  
New Generation ◽  
Cooling Air ◽  
The U.S

A new generation of auxiliary ships to enter the U.S. Navy (USN) fleet is the AOE-6 SUPPLY CLASS. These fast combat support ships conduct operations at sea as part of a Carrier Battle group to provide oil, aviation fuel, and ammunition to the carrier and her escorts. The SUPPLY CLASS is the first ship in the entire USN fleet to use a combined gas turbine and diesel generator cooling air intake system to cool its respective engine modules. The cooling air intake was designed this way to save on costs. As the ships in this class continued with operations and problems of insufficient supply of cooling air for the gas turbines modules started surfacing, the entire intake system required investigation and analysis. Since the gas turbines and diesel generators share a common cooling air trunk, they were competing for air. This paper will outline the tests that were performed to determine the problems, the recommended solutions, and the lessons learned from the investigations.

scholarly journals Experimental research in mechanic's field of control for further innovation in the hydraulic and electronic operated injection system

2019 ◽  
Vol 85 ◽  
pp. 08006 ◽  
Author(s):  
Iosif Ferenţi ◽  
Dan Opruţa ◽  
Doru Băldean
Keyword(s):  
Fuel Injection ◽  
Control Unit ◽  
Injection System ◽  
Minimal Amount ◽  
Operational Parameters ◽  
Complete Combustion ◽  
Sport Competition ◽  
Fuel Jet ◽  
Air Intake ◽  
Intake Pressure

In the present research paper is detailed an experimental work concerning Engine Control Unit (ECU) in order to trace predictive trend-lines regarding operational parameters such as ignition timing, fuel supply, injection duty, at more than ten engine speed regimes in the case of a powertrain for motor-sport competition, with distinct air pressures, injector status and spark advances. An experimental study of real values and trend-lines as well as actuator's output data was realized in order to point out electronic control unit's functional characteristics and to redefine the economic field with optimal combustion pressure, efficient mixture formation/burning and diminished emissions as a consequence of the proper measures. Air intake pressure influences the fundamental conditions for intake charge definition and for lambda level even prior to engine cycle beginning in the powertrain with port fuel injection (PFI). Lambda value expresses the operational quality in relation with the excess air intake compared to the minimal amount necessary for a complete combustion of fuel jet charge.

Exploration of Compact Combustors for Reheat Cycle Aero Engine Applications

2006 ◽  
Author(s):  
J. Zelina ◽  
D. T. Shouse ◽  
J. S. Stutrud ◽  
G. J. Sturgess ◽  
W. M. Roquemore
Keyword(s):  
Gas Turbine ◽  
Temperature Rise ◽  
Gas Turbines ◽  
Gas Turbine Engine ◽  
Operating Conditions ◽  
Combustion System ◽  
Turbine Engine ◽  
Lean Blowout ◽  
Power Extraction ◽  
Wide Range

An aero gas turbine engine has been proposed that uses a near-constant-temperature (NCT) cycle and an Inter-Turbine Burner (ITB) to provide large amounts of power extraction from the low-pressure turbine. This level of energy is achieved with a modest temperature rise across the ITB. The additional energy can be used to power a large geared fan for an ultra-high bypass ratio transport aircraft, or to drive an alternator for large amounts of electrical power extraction. Conventional gas turbines engines cannot drive ultra-large diameter fans without causing excessively high turbine temperatures, and cannot meet high power extraction demands without a loss of engine thrust. Reducing the size of the combustion system is key to make use of a NCT gas turbine cycle. Ultra-compact combustor (UCC) concepts are being explored experimentally. These systems use high swirl in a circumferential cavity about the engine centerline to enhance reaction rates via high cavity g-loading on the order of 3000 g’s. Any increase in reaction rate can be exploited to reduce combustor volume. The UCC design integrates compressor and turbine features which will enable a shorter and potentially less complex gas turbine engine. This paper will present experimental data of the Ultra-Compact Combustor (UCC) performance in vitiated flow. Vitiation levels were varied from 12–20% oxygen levels to simulate exhaust from the high pressure turbine (HPT). Experimental results from the ITB at atmospheric pressure indicate that the combustion system operates at 97–99% combustion efficiency over a wide range of operating conditions burning JP-8 +100 fuel. Flame lengths were extremely short, at about 50% of those seen in conventional systems. A wide range of operation is possible with lean blowout fuel-air ratio limits at 25–50% below the value of current systems. These results are significant because the ITB only requires a small (300°F) temperature rise for optimal power extraction, leading to operation of the ITB at near-lean-blowout limits of conventional combustor designs. This data lays the foundation for the design space required for future engine designs.

DLN Technology Update for the M701DA: Enhancing Vintage Gas Turbine Models With Latest Technology

2006 ◽  
Author(s):  
Satoshi Tanimura ◽  
Toyoaki Komori ◽  
Yasushi Fukuizumi ◽  
Scott Cloyd ◽  
David McDeed
Keyword(s):  
Gas Turbine ◽  
Design Process ◽  
Gas Turbines ◽  
Advanced Technology ◽  
Turbine Design ◽  
A Company

While the Gas Turbine design process is often focused on the development of the next advanced frame significant benefits can be achieved by retrofitting the latest technology in mature gas turbines model. This dissemination of advanced technology is a company philosophy of constant equipment enhancement. This paper will track the design process that is typically followed when enhancing vintage equipment. Also consideration will be discussed of transferring technology between 50 and 60 Hert frequency fleets.

scholarly journals A Low NOx Combustion System and a Ceramic Cross Flow Heat Exchanger for Small Gas Turbines

1987 ◽  
Author(s):  
Siegfried Förster ◽  
Peter Quell
Keyword(s):  
Heat Exchanger ◽  
Gas Turbines ◽  
Cross Flow ◽  
Fuel Oil ◽  
Actual State ◽  
Combustion System ◽  
Air Temperatures ◽  
Shaft Power ◽  
Flow Heat ◽  
Gas Turbine Cycle

A new low NOx oil-combustion system with superheated steam fuel evaporation prior to combustion has been found especially feasible for open cycle gas turbines with high turbine inlet temperatures and ceramic cross flow heat exchanger. The actual state of development of both the low NOx light fuel-oil combustion system and ceramic heat exchanger elements, especially the cross flow type, is outlined in this paper. The use of this combustion system results in considerably lower combustion temperatures in the primary combustion zone, reducing the NOx-production even at high air temperatures when the air is preheated in the heat exchanger. The water vapour used for the evaporation of the fuel oil before combustion has an improving effect on the cycle efficiency comparable to the Cheng-dual-fluid-cycle. Illustrative evaluations for a gas turbine cycle for a shaft power of 70 kW are given.

scholarly journals Gas Turbine Compressor Configuration Analysis for Production and Efficiency Optimization at PT Saka Indonesia Pangkah Ltd.

2021 ◽  
Vol 927 (1) ◽  
pp. 012031
Author(s):  
Muhammad Arif Afandy ◽  
Ifani P Ramadhani ◽  
Totok R Biyanto
Keyword(s):  
Gas Turbine ◽  
Fuel Consumption ◽  
Gas Turbines ◽  
Oil And Gas ◽  
Liquid Hydrocarbon ◽  
Operating Point ◽  
Design Calculation ◽  
Shaft Power ◽  
Turbine Shaft ◽  
And Performance

Abstract Gas Turbine Compressors are used by Saka Indonesia Pangkah Ltd. in upstream oil and gas facilities either to boost hydrocarbon products to downstream facilities or to lift liquid hydrocarbon as a common artificial method. As production rate declining leads to gas supply deficiency to the compressors, the operating point move to surge line away from the best efficiency point. Gas feed shortage affecting the compressor’s performance which contributed to head and flow capacity. This condition is then calculated and simulated using UNISIM Design Simulator to get optimum configuration results. The simulation was performed at the same gas turbine shaft power output of each compressor. Two cases of centrifugal compressors configuration with different functions and performance are studied. Due to process dynamic conditions, constraint parameter is considered as per desired operating point. This paper also analyses techno-economic aspects between individual and serial pipelines arrangement of the two compressors by evaluating operational data and design calculation. Subsequently, this study produces assessment observations associated with the compressor performance both in individual and serial configuration and eventually analyses the rate of fuel consumption in the gas turbines as the main driver. The case study shows serial arrangement between MPC-1 and GLC with same gas turbine shaft power as individual configuration can reduce fuel consumption up to 47 kg/hr. It saves as much as USD 7,569.96 per day at low demand and USD 7,569.96 at high-demand cases.

Sign in / Sign up

Export Citation Format

Share Document