Start Fuel Schedule Enhancements for the ETF40B Gas Turbine Engine

2009 ◽  
Author(s):  
Joseph L. Simonetti ◽  
Joseph H. McMurry
Keyword(s):  
Gas Turbine ◽  
Diesel Fuel ◽  
Test Procedure ◽  
Gas Turbine Engine ◽  
Acceptance Test ◽  
Fuel System ◽  
Turbine Engine ◽  
Fuel Flow ◽  
Us Navy ◽  
Engine Start

Gross starting characteristics of the Vericor Power Systems ETF40B gas turbine engine utilizing diesel fuel for the Republic of Korea Navy LSF-II application indicate inconsistent starting performance, especially in cold ambient temperatures. There is also evidence that cold starting inconsistencies exist on the US Navy LCAC installation of the ETF40B engine. The inconsistencies include late light-offs, failed starts, excessive exhaust smoke, detonative ignition and excessive commanded fuel flow by the full authority digital engine control (FADEC). The starting anomalies experienced on US Navy LCAC have ultimately resulted in the addition of starting requirements to the production engine acceptance test procedure. A detailed review of historical information regarding the TF40B fuel system characteristics resulted in the basis for establishing revised LFMV calibration values and revised FADEC engine start fuel scheduling. Additionally, this review indicated the need for fuel system flow/pressure measurements in order to establish current characteristics and to help refine component requirements and changes (as appropriate). These measurements are required over the entire engine starting and operating range. Cold ambient temperature start testing was performed to establish the engine start characteristics on JP5/JET A fuels with the existing and revised LFMV calibrations. A revised start schedule was developed that provided a reliable, stable starting characteristic (reliable first attempt starting, reducing smoking on starts, eliminating detonative ignition, minimizing large variations in commanded fuel flow during starting). The fuel system pressures and flows were fully characterized in the start and operating regime and start testing validation was performed on Diesel Fuel.

An Enhanced Gas Turbine Engine Laboratory: A Learning Platform Supporting an Undergraduate Engineering Curriculum

2019 ◽  
Author(s):  
Andrew T. Bellocchio ◽  
Michael J. Benson ◽  
Bret P. Van Poppel ◽  
Seth A. Norberg ◽  
Ryan Benz
Keyword(s):  
Data Acquisition ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Complete Analysis ◽  
Turbine Engine ◽  
Laboratory Experience ◽  
Operating Range ◽  
Fuel Flow ◽  
Learning Platform ◽  
Original Laboratory

Abstract A gas turbine engine has supported the U.S. Military Academy’s mechanical engineering program for nearly three decades. Recent, substantial enhancements to the engine, controls, and data acquisition systems greatly increased the student experience by leveraging its broad capabilities beyond the original laboratory learning objectives. In this way, the laboratory served as a learning platform for more than just instruction on gas turbine fundamentals and the Brayton cycle. The engine is a refurbished auxiliary power unit from Pratt & Whitney Aeropower, installed in the Embrauer 120 and similar to a unit installed on a U.S. Army helicopter. Whereas the original laboratory experience permitted students to test the engine at three different loads applied by a water brake dynamometer, the revised experience allowed for a broader range of test conditions. The original laboratory included single point measurements of three temperatures and two pressures, along with the fuel flow rate, dynamometer torque, and engine speed. The revised laboratory allowed the user to vary bleed air and engine loads across an operational envelope at a user-specified acquisition rate. The improved data acquisition system used LabVIEW™ and included multiple state sensors for pressure, temperature, fuel flow, bleed air, and dynamometer performance, thereby enabling a more complete analysis by accounting for the energy transported by bleed airflow and absorbed by the water brake. Students then quantified the uncertainty in their measurements and analysis. The new emphasis on uncertainty quantification, part of a program-level initiative, challenged students’ notion of “substitute and solve” while also familiarizing them with large, experimental data sets. The re-envisioned laboratory raised the students’ level in the cognitive domain and served as their premier engine experience. Rather than merely observing engine adjustments across a small range of conditions, students designed their own laboratory experience. With the updated approach, students viewed a graphic of the turbine’s laboratory operating range and chose the key variables of interest — selecting data points within the laboratory operating range — and then justified their selections. The enhanced experience added analysis of flow exergy and exergetic efficiency. The exercise also challenged students to hypothesize why actual turbine performance was less than predicted and determine sources of error and uncertainty. Moreover, the new laboratory offers opportunities to expand the turbine engine’s utility from supporting a single thermal-fluids course to a multidisciplinary learning platform. Concluding remarks address concepts for augmenting course instruction in other courses within the curriculum, including heat transfer, mechanical vibrations, and dynamic modeling and controls.

scholarly journals Aircraft Gas Turbine Engine Health Monitoring System by Real Flight Data

2018 ◽  
Vol 2018 ◽  
pp. 1-12 ◽  
Author(s):  
Mustagime Tülin Yildirim ◽  
Bülent Kurt
Keyword(s):  
Gas Turbine ◽  
Engine Performance ◽  
Aircraft Engine ◽  
Gas Turbine Engine ◽  
Gas Temperature ◽  
Turbine Engine ◽  
Fuel Flow ◽  
The Status ◽  
Performance Deterioration ◽  
Artificial Neural Network Ann

Modern condition monitoring-based methods are used to reduce maintenance costs, increase aircraft safety, and reduce fuel consumption. In the literature, parameters such as engine fan speeds, vibration, oil pressure, oil temperature, exhaust gas temperature (EGT), and fuel flow are used to determine performance deterioration in gas turbine engines. In this study, a new model was developed to get information about the gas turbine engine’s condition. For this model, multiple regression analysis was carried out to determine the effect of the flight parameters on the EGT parameter and the artificial neural network (ANN) method was used in the identification of EGT parameter. At the end of the study, a network that predicts the EGT parameter with the smallest margin of error has been developed. An interface for instant monitoring of the status of the aircraft engine has been designed in MATLAB Simulink. Any performance degradation that may occur in the aircraft’s gas turbine engine can be easily detected graphically or by the engine performance deterioration value. Also, it has been indicated that it could be a new indicator that informs the pilots in the event of a fault in the sensor of the EGT parameter that they monitor while flying.

U.S. Navy Qualification of a GE LM2500+ Gas Turbine Engine

2005 ◽  
Author(s):  
Shaun Hatcher ◽  
Tom Batory ◽  
Robert Neff ◽  
Pat Kane
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
High Impact ◽  
Endurance Test ◽  
Turbine Engine ◽  
Shock Testing ◽  
Us Navy ◽  
Post Shock ◽  
Overall Performance ◽  
Test Requirements

This report is a comprehensive document citing the events pertaining to the qualification of the GE LM2500+ gas turbine engine for US Navy Service. The purpose of this report is to serve as documentation of the entire Qualification process that includes the 500-hour Rating Qualification Test and subsequent teardown inspection, High Impact Shock Testing, and the subsequent 100-hour post shock endurance test and teardown inspection. This report includes an assessment of the overall performance of the engine, General Electric’s capacity to meet specified test requirements, any questions or concerns that may have arisen during testing, and a conclusive statement about the outcome of the tests.

scholarly journals Salt Ingestion Test of the AGT 1500 Recuperated Automotive Gas Turbine

1988 ◽  
Author(s):  
Thomas M. Bodman ◽  
Thomas P. Priore
Keyword(s):  
Gas Turbine ◽  
Systems Engineering ◽  
Diesel Fuel ◽  
Marine Corps ◽  
Gas Turbine Engine ◽  
Significant Loss ◽  
Turbine Engine ◽  
Naval Ship ◽  
The U.S

A salt ingestion test was performed on the AGT 1500 recuperated automotive gas turbine engine at the Naval Ship Systems Engineering Station (NAVSSES) for the U.S. Marine Corps. The Marine Corps was concerned about the AGT 1500’s ability to tolerate their amphibious and maritime environments. The AGT 1500 was operated for two 450 hour endurance runs burning Navy diesel fuel and ingesting aerosol salt. It suffered no failures or significant loss of power as a result of the ingested salt or operations with Navy diesel fuel.

scholarly journals Rancang Bangun Oil System untuk Turbocharger Gas Turbine Engine Dengan Inducer Diameter 1,75 Inch

2021 ◽  
Vol 14 (01) ◽  
pp. 66-76
Author(s):  
Noval Dwi Kurnianto ◽  
Wira Gauthama ◽  
Zulham Hidayat
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Critical Pressure ◽  
Gas Turbine Engine ◽  
Metal Contact ◽  
Fuel System ◽  
Turbine Engine ◽  
System Combustion

Rancang bangun mesin turbin gas dimulai dengan mengidentifikasi beberapa komponen yang dibutuhkan dalam membangun sebuah mesin turbin gas. Turbocharger yang terdiri dari kompresor dan turbin sebagai penyusun utama komponen ini diambil untuk dijadikan Kompresor dan turbin  mesin turbin gas yang juga merupakan unsur utama dalam sebuah mesin turbin gas. Agar sebuah mesin turbin gas dapat beroperasi maka perlu dirancang beberapa system pendukung seperti Oil System, Fuel System, Ignation System, Combustion Chamber dan beberapa system yang lain. Pada perancangan ini, penulis mendapat bagian dalam perancangan Sistem pelumas (Oil System) dimana tantangan yang dihadapi adalah mendapatkan jenis oil yang tepat untuk mesin turbin gas yang akan dibangun. Adapun  rumusan masalah dalam perancangan system pelumas ini antara lain bagaimana menentukan viskositas pelumas yang digunakan, menghitung critical pressure bearing, menghitung jumlah pelumas yang digunakan, menghitung head pompa dan menghitung kapasitas reservoir yang digunakan. Output akhir yang dihasilkan dari perancangan ini adalah  suplai oli yang mampu untuk melumasi shaft bearing pada turbocharger sehingga tidak terjadi overheating yang menyebabkan keausan serta metal to metal contact. Dari hasil perhitungan, didapatkan tekanan oli sebesar 37 psi yang diperlukan untuk melumasi shaft bearing pada turbocharger. Dan dihasilkan pembakaran yang continuous.

A Model-Based Approach to the Control of an Aircraft Gas Turbine Engine

1993 ◽  
Author(s):  
Oliver F. Qi ◽  
N. R. L. Maccallum
Keyword(s):  
Gas Turbine ◽  
Control Variable ◽  
Gas Turbine Engine ◽  
Observer Design ◽  
Nonlinear Controller ◽  
Flow Distortion ◽  
Turbine Engine ◽  
Control Approach ◽  
Model Based ◽  
Fuel Flow

This paper describes a model-based control approach to synthesizing a nonlinear controller for a single-spool gas turbine engine. Since the main control variable, engine thrust, cannot be directly measured, a model-based observer is constructed using a nonlinear model of the engine in order to provide an on-line estimation of the thrust for feedback control. Both proportional and proportional-integral (PI) observers have been used in the model-based observer design. The latter is intended to provide a robust estimation in the event of modeling errors. The controls are the fuel flow and final nozzle area, and the control structure is the PI controller designed using the KQ (K-matrix compensator, Q-desired response) multivariable design technique. A study has been made of the model-based observer control scheme when the engine is subjected to the disturbance of inlet flow distortion. The results are shown to be acceptable in terms of the thrust response and the transient trajectory on the compressor characteristic.

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