The V.P.I. Gas Turbine and Turbomachinery Research Laboratory

1977 ◽  
Author(s):  
W. F. O’Brien ◽  
R. R. Jones ◽  
H. L. Moses ◽  
J. F. Sparks
Keyword(s):  
Gas Turbine ◽  
Research Laboratory ◽  
High Speed ◽  
Test Cell ◽  
Gas Generator ◽  
Related Research ◽  
Coupled Mode ◽  
Governing System ◽  
Turboshaft Engine

A recently completed facility for high-speed turbomachinery and gas turbine related research is described. A test cell houses a 3000 hp turboshaft engine which is capable of driving research rotors in a direct-coupled mode at speeds to 17,000 rpm. Gearboxes provide for reverse drive and speeds from 8000 to 24,000 rpm. An automatic governing system controls gas generator and load speeds, and provides overspeed protection. Research instrumentation includes on-rotor telemetry equipment for transmission of data from research rotors.

The Co-Turboshaft: A Novel Gas Turbine Powerplant for Heavy Equipment

1979 ◽  
Author(s):  
D. A. J. Millar ◽  
M. S. Chappell ◽  
R. Okelah
Keyword(s):  
Gas Turbine ◽  
Control Strategies ◽  
Output Shaft ◽  
Speed Ratio ◽  
Inlet Temperature ◽  
Gas Generator ◽  
Turbine Engine ◽  
Engine Torque ◽  
Performance Effects ◽  
Turboshaft Engine

A major advantage of the two-shaft gas turbine as a prime mover is the steep torque-speed characteristic, so that the stall torque is typically twice the design torque. The co-turboshaft engine has a torque-speed curve which can be more than twice as steep as the conventional engine, so that only a rudimentary transmission would be required for normal operations. The co-turboshaft gas turbine engine has a co-rotating compressor case which is geared, together with the free power turbine, to the output shaft. As load increases and output shaft speed decreases, the effective gas generator speed increases, with no increase in rotor speed, and the power output rises. The engine has a torque-speed curve with up to four times the slope of a conventional free shaft turbine engine torque curve. This paper reviews results of testing a compressor with a co-rotating casing, and presents the results of simulating a typical engine using a hybrid computer to predict engine steady state performance. Effects of different design choices of compressor casing speed ratio are shown on engine torque, power and turbine inlet temperature characteristics. Control strategies for some possible applications, such as off-road vehicles and construction equipment, are discussed in relation to their likely duty cycles.

Marine Gas Turbine Package for the Korean Navy PKX Program

2008 ◽  
Author(s):  
Naytoe Aye ◽  
Glenn McAndrews ◽  
Bob Mendenhall
Keyword(s):  
Gas Turbine ◽  
High Speed ◽  
System Development ◽  
Test Cell ◽  
Production Test ◽  
Prime Mover ◽  
Sea Trial ◽  
Design Evolution ◽  
Marine Propulsion ◽  
Component Development

GE together with MTSI, Woodward, and Bibby Transmissions, has developed and delivered a compact gas turbine package for the Korean Navy. The prime mover is GE’s LM500 engine rated at 5500 shp. Remarkably, the period of execution was only 16 months including the development and construction of the production test cell. The paper will examine all phases of the propulsion system development from ship integration to sea trial results (scheduled for Spring 2008). Of particular interest is the design evolution of the high speed coupling shaft (HSCS). Of all of the component development activities, the HSCS was the most challenging. Progress in this particular area will benefit future marine propulsion programs requiring shock qualification.

Magnetoelastic Torquemeter System for LCAC Hovercraft Turboshaft Engine Monitoring and Control

2012 ◽  
Author(s):  
Ryan J. Kari ◽  
Tej Patel ◽  
Benjamin Canilang ◽  
Americo Bonafede ◽  
Sami Bitar ◽  
...  
Keyword(s):  
Gas Turbine ◽  
High Speed ◽  
Optimal Operation ◽  
Monitoring And Control ◽  
Readiness Level ◽  
Air Cushion ◽  
Turboshaft Engine ◽  
The Right ◽  
General Architecture ◽  
And Control

This paper presents the development of a magnetoelastic torque-meter for use on the Landing Craft Air Cushion (LCAC) hovercraft’s high speed gas turbine engines. As the gas turbine can produce in excess of the nominal torque limit of the right angle gearbox, torque limiting is required. Limiting torque based on torque tables (as is done currently) penalizes the overall performance of the majority of the fleet due to a significant variance in engine output horsepower. This sub-optimal operation of the craft could be overcome by measuring actual torque produced by each engine with a torque-meter; however conventional torque-meter designs were deemed impractical to retrofit due to the design requirements, and issues with integration and reliability / maintainability. An in-depth search by the US Navy identified a torque-meter concept utilizing magnetoelastic polarized band technology. The aim of this paper is to: (i) outline the general architecture of the system, (ii) highlight the performance of the torque-meter developed for the LCAC, (iii) describe the efforts that helped to mature this technology to Technology Readiness Level 8 and to transition it from motorsport applications to use on the LCAC, and (iv) summarize the initial results of the torque-meter system validation obtained through dynamometer tests on the engine and craft tests on the LCAC.

The Development and Testing of the MFT8 Gas Turbine

1994 ◽  
Author(s):  
K. Akagi ◽  
K. Uematsu ◽  
T. Yashlki ◽  
J. Horner ◽  
K. Krivichi
Keyword(s):  
Gas Turbine ◽  
High Speed ◽  
New Product ◽  
Simulation Approach ◽  
Gas Generator ◽  
Design Philosophy ◽  
Power Turbine ◽  
Power Testing

The MFT8 rated at 33,000 ps has been developed by Mitsubishi Heavy Industries (MHI) in support of the Techno SuperLiner (TSL) R&D program. The MFT8 combines the GG8 Gas Generator from Pratt & Whitney/Turbo Power & Marine with a new 3 stage, 5000 RPM, cantilevered rotor power turbine which was designed by MHI specifically for the TSL program and other high speed marine craft applications. This paper illustrates the versatility that an independent, two shaft gas generator offers in developing a new product for a specific application. The text describes the design philosophy, power turbine and controls simulation approach followed by the presentation of the model and power testing results as compared to the predicted parameters.

scholarly journals Garrett’s Turboshaft Engines and Technologies for the 1990s

1990 ◽  
Author(s):  
Terry Pyle ◽  
Dan Aldrich
Keyword(s):  
Gas Turbine ◽  
High Performance ◽  
New Technologies ◽  
Product Line ◽  
Superior Performance ◽  
Medium Size ◽  
Gas Generator ◽  
Full Spectrum ◽  
Turbine Engine ◽  
Turboshaft Engine

Garrett Engine Division of Allied-Signal Aerospace, Inc., which supplies small-to-medium size gas turbine propulsion engines to the fixed-wing aviation market, is expanding its product line to include the small-to-medium turboshaft engine for the rotary wing (helicopter) aviation market. The recent win of the T800-LHT-800 down-select formed a firm foundation for this expansion. Garrett is developing the T800 in a partnership with the Allison Gas Turbine Division of General Motors Corporation, under the company name of Light Helicopter Turbine Engine Company (LHTEC). The T800 turboshaft engine (1300-shp, 1000-kW class), which has superior performance in this power class (10 to 30 percent better specific fuel consumption and power-to-weight than current production turboshaft engines), is designed to power the U.S. Army’s LHX light attack helicopter. Garrett is pursuing complementary technologies focused on serving a full spectrum of turboshaft engine requirements for the 1990s and beyond. Garrett is also teamed with General Electric Aircraft Engines (GEAE), for the Joint Turbine Advanced Gas Generator (JTAGG) demonstrator program. JTAGG supports the Integrated High Performance Turbine Engine Technology (IHPTET) initiative of doubling propulsion system capabilities by the year 2003. New technologies incorporated in the T800, and emerging technologies and concepts applicable to future turboshafts, are discussed.

Developing of a Lubricant Oil for the Ship Gas Turbine of Reducer

2012 ◽  
Vol 629 ◽  
pp. 339-343
Author(s):  
Fu Chuan Huang ◽  
Xing Zhong Tang ◽  
Man Rong Su ◽  
Zhao Xia Lu ◽  
You Cheng Xiao ◽  
...  
Keyword(s):  
Gas Turbine ◽  
High Speed ◽  
Salt Spray ◽  
Heat Engine ◽  
The United States ◽  
Heavy Duty ◽  
Gas Generator ◽  
Base Oil ◽  
Turbine Oil ◽  
Continuous Rotation

The combination of ship gas turbine working at special environment, this article pass through the study of base oil and composite additive, developed an application marine environment of the ship gas turbine reducer lubricants. According to comprehensive performance assessment, the product has excellent high-temperature anti-oxidant, anti-wear, corrosion inhibition and anti-foam performance. The indicators have reached the requirements. With the development of China's ship gas turbine technology, especially UGT25000 ship gas turbine technology is imported from Ukraine, as well as the recent introduction of the GE LM2500 + G4 Series of technology for power plant of construction. The localization of the supporting facilities are growing louder, there is a strong market rigid demand. Ship gas turbine must be one of the trends of the development of Marine Power. Ship gas turbine due to light weight, small size, stand-alone power, fast start; less pollution, vibration, high thermal efficiency and gas initial temperature, it is easy to realize the cascade of energy use, economy, received widespread attention and application. China's ship gas turbine of modification and design draw the aero-engine, ship gas turbine is a continuous rotation of the impeller mechanical heat engine; it is mainly composed by three parts of the compressor, gas generator and gas turbine. Ships generally use diesel (fuel have heavy trend, the heavy diesel oil or No. 200 heavy oil will be used) as fuel, in order to adapt the ship gas turbine, ship gas turbine need to transform, particularly its' lubrication system [1]. Foreign aviation gas engine lubricants are based on the U.S. standard as a reference, due to the differences of using purpose and fuel, so that the ship gas turbine oil has different requirements. Since ship gas Turbine Technology started late in China, the ship gas turbine core engine technology patents come from the United States, Russia and Ukraine, so the use of gas turbine lubricants, as well as matching accessories and other standards, which are more or less directed reference to refer to the original foreign standards [2,3]. We have never been established using standard ship gas turbine oil. Ship gas turbine apply to the special conditions (high humidity, salt spray, etc.), the ship gas turbine of lubrication has a higher demand, particularly for the ship gas turbine reducer of lubrication. The ship gas turbine reducer work in the low-speed heavy-duty and high-speed heavy-duty , high strength, high shear conditions, how ensure the ship gas turbine reducer to normal work is very important at high load conditions. In this regard, developing of a ship gas turbine reducer lubricant is very necessary.

PGT25+G4 Gas Turbine Development, Validation and Operating Experience

2008 ◽  
Author(s):  
Roger De Meo ◽  
Michele D’Ercole ◽  
Alessandro Russo ◽  
Francesco Gamberi ◽  
Francesco Gravame ◽  
...  
Keyword(s):  
Power Generation ◽  
Gas Turbine ◽  
High Speed ◽  
Operating Experience ◽  
Quality Parameters ◽  
Lessons Learned ◽  
Gas Generator ◽  
Test Program ◽  
Power Turbine ◽  
Extensive Test

The PGT25+G4 gas turbine, latest in GE Infrastructure Oil&Gas PGT25 two-shaft aeroderivative family, is a 34 MW-class gas turbine for mechanical drive and power generation applications and maintains the same efficiency and availability of the previous PGT25+. The PGT25+G4 was validated through an extensive test program, which included some key test-rigs such as the full-scale LM2500+G4 Gas Generator test and other component tests, in advance of the First Engine to Test (FETT). The FETT included an equivalent-to-production configuration package (gas turbine, auxiliaries and control system), ran in a dedicated area in GE Oil&Gas Test Facilities to validate the machine for both mechanical drive and power generation applications. All critical-to-quality parameters of the HSPT (High Speed Power Turbine) were investigated, such as turbine gas path components temperatures and stresses, PT performances and PT operability when coupled with the LM2500+G4 Gas Generator. First production unit is currently in operation at Alliance Pipeline Canada Windfall 1 Compression Station. This paper describes the gas turbine main features, how the test program was built and discusses FETT results. Moreover, gas turbine field operation experience and lessons learned are presented.

scholarly journals PZL-10 Turboshaft Engine–System Design Review

2019 ◽  
Vol 26 (1) ◽  
pp. 23-29
Author(s):  
Michal Czarnecki ◽  
John Olsen ◽  
Ruixian Ma
Keyword(s):  
Gas Turbine ◽  
Pressure Ratio ◽  
Axial Compressor ◽  
Performance Model ◽  
Inlet Temperature ◽  
Gas Generator ◽  
Design Bureau ◽  
Turbine Engine ◽  
Engine Design ◽  
Turboshaft Engine

Abstract The PZL – 10-turboshaft gas turbine engine is straight derivative of GTD-10 turboshaft design by OKMB (Omsk Engine Design Bureau). Prototype engine first run take place in 1968. Selected engine is interested platform to modify due gas generator layout 6A+R-2, which is modern. For example axial compressor design from successful Klimov designs TB2-117 (10A-2-2) or TB3-117 (12A-2-2) become obsolete in favour to TB7-117B (5A+R-2-2). In comparison to competitive engines: Klimov TB3-117 (1974 – Mi-14/17/24), General Electric T-700 (1970 – UH60/AH64), Turbomeca Makila (1976 – II225M) the PZL-10 engine design is limited by asymmetric power turbine design layout. This layout is common to early turboshaft design such as Soloview D-25V (Mil-6 power plant). Presented article review base engine configuration (6A+R+2+1). Proposed modifications are divided into different variants in terms of design complexity. Simplest variant is limited to increase turbine inlet temperature (TIT) by safe margin. Advanced configuration replace engine layout to 5A+R+2-2 and increase engine compressor pressure ratio to 9.4:1. Upgraded configuration after modification offers increase of generated power by 28% and SFC reduction by 9% – validated by gas turbine performance model. Design proposal corresponds to a major trend of increasing available power for helicopter engines – Mi-8T to Mi-8MT – 46%, H225M – Makila 1A to 1A2 — 9%), Makila 1A2 to Makila 2-25%.

Transformation of an Aviation Turboshaft Engine Into a Experimental Jet Engine for Laboratory Testing Unstable Radial Compressor Work

2014 ◽  
Author(s):  
Marián Hocko ◽  
Jiri Polansky
Keyword(s):  
Gas Turbine ◽  
Experimental Testing ◽  
Thermodynamic Characteristics ◽  
Power Generator ◽  
Jet Engine ◽  
Radial Compressor ◽  
Laboratory Device ◽  
Research And Education ◽  
Turboshaft Engine ◽  
Electronic Elements

The article deals with the use of a small aviation turboshaft engine for laboratory purposes. This study describes its transformation into an experimental device for research and education. Various constructional, technological and controlling modifications and settings of the gas turbine test stand were carried out and tested on a stationary configuration. The stationary system can be used as a small backup power generator or as a drive unit for a compressor, pump, etc. New control systems, electronic elements and methods of measuring rotations, pressure and temperature are tested for educational and research purposes. The study includes a schematic description of modelling measurements and subsequent numerical evaluation of the thermodynamic characteristics of the cycle in an experimental gas turbine. The laboratory device presented here is, thanks to technological, material and thermodynamic research, suitable for educating and testing the knowledge of future aviation and mechanical engineers. The content of the article is a description of the use of transformed small turboshaft engine into small jet engine by means of experimental testing of unstable work of the radial compressor under laboratory conditions.

scholarly journals Wall Temperature Measurements in Gas Turbine Combustors With Thermographic Phosphors

2018 ◽  
Vol 141 (4) ◽  
Author(s):  
Patrick Nau ◽  
Zhiyao Yin ◽  
Oliver Lammel ◽  
Wolfgang Meier
Keyword(s):  
Gas Turbine ◽  
Wall Temperature ◽  
Gas Turbines ◽  
High Speed ◽  
Bluff Body ◽  
Temperature Measurements ◽  
Transient Temperature ◽  
High Time Resolution ◽  
Ceramic Surface ◽  
Precessing Vortex Core

Phosphor thermometry has been developed for wall temperature measurements in gas turbines and gas turbine model combustors. An array of phosphors has been examined in detail for spatially and temporally resolved surface temperature measurements. Two examples are provided, one at high pressure (8 bar) and high temperature and one at atmospheric pressure with high time resolution. To study the feasibility of this technique for full-scale gas turbine applications, a high momentum confined jet combustor at 8 bar was used. Successful measurements up to 1700 K on a ceramic surface are shown with good accuracy. In the same combustor, temperatures on the combustor quartz walls were measured, which can be used as boundary conditions for numerical simulations. An atmospheric swirl-stabilized flame was used to study transient temperature changes on the bluff body. For this purpose, a high-speed setup (1 kHz) was used to measure the wall temperatures at an operating condition where the flame switches between being attached (M-flame) and being lifted (V-flame) (bistable). The influence of a precessing vortex core (PVC) present during M-flame periods is identified on the bluff body tip, but not at positions further inside the nozzle.

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