The Westinghouse/Rolls-Royce WR-21 Gas Turbine Variable Area Power Turbine Design

1995 ◽  
Author(s):  
John C. Cox ◽  
David Hutchinson ◽  
James I. Oswald
Keyword(s):  
Gas Turbine ◽  
Mechanical Design ◽  
Thermodynamic Cycle ◽  
Low Flow ◽  
Good Reliability ◽  
Precise Control ◽  
Power Turbine ◽  
Exhaust Heat ◽  
Full Power ◽  
Turbine Capacity

The Westinghouse/Rolls-Royce WR-21 marine gas turbine with an intercooled, recuperated thermodynamic cycle utilises exhaust heat to provide excellent efficiency not only at full power but also at part power. Vital to the success of the engine and the optimisation of fuel consumption is the Variable Area Nozzle (VAN) which is used to control turbine capacity across the power range. By continuously monitoring and controlling turbine capacity, the heat recovered by the recuperator is optimised across the power range. The efficiency of the power turbine variable stage at low power (low flow) and its ability to deliver full power (high flow) is vital to the success of the engine. Success also requires precise control of the variable vane, easy maintenance and good reliability in a hot, mechanically hostile environment. This paper describes the aerodynamic and mechanical design, rig verification and early engine experience of the variable power turbine stage.

Capacity Matching of Aeroderivative Gas Generator With Free Power Turbine: Challenges, Uncertainties, and Opportunities

2019 ◽  
Author(s):  
Deepak Thirumurthy ◽  
Jose Carlos Casado Coca ◽  
Kanishka Suraweera
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Systems Approach ◽  
Gas Generator ◽  
Performance Guarantees ◽  
Design Variables ◽  
Performance Trends ◽  
Power Turbine ◽  
Parameter Matching ◽  
Turbine Capacity

Abstract For gas turbines with free power turbines, the capacity or flow parameter matching is of prime importance. Accurately matched capacity enables the gas turbine to run at its optimum conditions. This ensures maximum component efficiencies, and optimum shaft speeds within mechanical limits. This paper presents the challenges, uncertainties, and opportunities associated with an accurate matching of a generic two-shaft aeroderivative HP-LP gas generator with the free power turbine. Additionally, generic performance trends, uncertainty quantification, and results from the verification program are also discussed. These results are necessary to ensure that the final free power turbine capacity is within the allowable range and hence the product meets the performance guarantees. The sensitivity of free power turbine capacity to various design variables such as the vane throat area, vane trailing edge size, and manufacturing tolerance is presented. In addition, issues that may arise due to not meeting the target capacity are also discussed. To conclude, in addition to design, analysis, and statistical studies, a system-of-systems approach is mandatory to meet the allowed variation in the free power turbine capacity and hence the desired gas turbine performance.

Solar Turbines Incorporated “Taurus 60” Gas Turbine Development

1994 ◽  
Author(s):  
Vern Van Leuven
Keyword(s):  
Gas Turbine ◽  
Mechanical Design ◽  
Selection Process ◽  
Thermodynamic Cycle ◽  
Turbine Rotor ◽  
Original Design ◽  
Design Changes ◽  
Third Stage ◽  
Final Design ◽  
Design Selection

The Taurus gas turbine was first introduced in 1989 with ratings of 6200 HP for single shaft and 6500 HP for twin shaft configurations. A new design of the single shaft third stage turbine rotor and exhaust diffuser brought its power to 6500 HP in 1991. A program was initiated early in 1992 to identify opportunities to further optimize performance of the Taurus. Thorough investigation of performance sensitivity to thermodynamic cycle parameters has resulted in significant improvement over the original design with no change in firing temperature. Aerodynamic and mechanical design changes were implemented in 1993 which raised Taurus performance to 7000 HP and 32% thermal efficiency. Selection of the final design configuration was the outcome of performance maximization versus cost increase, durability risk and loss of commonality with previous engines. This paper details these changes and the design selection process.

Thermodynamic and Mechanical Design Concept for Micro-Turbojet to Micro-Turboshaft Engine Conversion

2020 ◽  
Author(s):  
Christoph Öttl ◽  
Reinhard Willinger
Keyword(s):  
Mechanical Design ◽  
Thermodynamic Cycle ◽  
Design Concept ◽  
Specific Power ◽  
Gas Generator ◽  
Cycle Simulation ◽  
Turbojet Engine ◽  
Specific Power Output ◽  
Power Turbine ◽  
Turboshaft Engine

Abstract In this work, a design concept for micro-turbojet to micro-turboshaft engine conversion is presented. This is motivated by a lack of available micro-turboshaft engines which is shown in the market survey conducted. Thus, the presented concept deals with the conversion of an existing micro-turbojet engine to a micro-turboshaft engine for a specific power output. The conversion is shown using the micro-turbojet engine OLYMPUS HP from AMT Netherlands. Furthermore, the simultaneously developed analytical preliminary design of the additional single-stage power turbine is shown besides a thermodynamic cycle simulation. This has been done to obtain the unknown gas generator outlet condition which is similar to the power turbine’s inlet condition. Within the cycle calculation, occurring losses due to the small dimensions have also been considered. During the design process, different combinations of work coefficient and mean diameter of the power turbine were investigated to minimize the required gear box ratio for a given rotor speed in terms of weight minimization. To keep losses in the power turbine low, the preliminary blade row has finally been improved using CFD calculations.

scholarly journals Development and Field Experience of a New 29000 HP Gas Turbine

1980 ◽  
Author(s):  
J. K. Hubbard ◽  
C. Austin
Keyword(s):  
Gas Turbine ◽  
Field Experience ◽  
Performance Test ◽  
High Efficiency ◽  
Test Facility ◽  
Gas Generator ◽  
Initial Field ◽  
Power Turbine ◽  
Exhaust Heat ◽  
Gas Turbine Exhaust

The paper describes the development and initial field experience with a new high efficiency 26,000/30,000 hp gas turbine. Exhaust heat from the power turbine was used to boost the installation thermal efficiency and provide icing protection for the inlet. Wherever possible, proven power turbine design concepts were combined with the advances of a “second generation” aircraft derivative gas generator to produce a reliable machine which was introduced with a minimum of development time. To assure field success, a special test facility was constructed and the unit subjected to a full load mechanical and performance test under simulated field condition.

Development of Hybrid Power Systems Based on Direct Fuel Cell/Turbine Cycle

2005 ◽  
Author(s):  
Hossein Ghezel-Ayagh ◽  
Robert Sanderson ◽  
Jim Walzak
Keyword(s):  
Fuel Cell ◽  
Power Systems ◽  
Gas Turbine ◽  
Hybrid Systems ◽  
Gas Turbines ◽  
Power Plants ◽  
High Efficiency ◽  
Mechanical Design ◽  
Thermodynamic Cycle ◽  
Hybrid Power

FuelCell Energy Inc. (FCE) is developing ultra high efficiency Direct FuelCell/Turbine® (DFC/T®) hybrid power plants. Present activities are focused both on the demonstration of the DFC/T concept in small packaged hybrid power generation units for distributed generation, and the design of multi-megawatt (Multi-MW) hybrid systems for the wholesale electric power market. The development of Multi-MW DFC/T systems has been focused on the on the design of power plants with efficiencies approaching 75% (LHV of natural gas). The design efforts included thermodynamic cycle analysis of key gas turbine parameters such as compression ratio. The power plant designs were studied for near-term deployment utilizing the existing commercially available gas turbines and long-term deployment requiring advanced gas turbine technologies. A new fuel cell cluster concept was developed for mechanical design of Multi-MW systems. The concept utilizes the existing one-MW fuel cell modules as the building block for the Multi-MW hybrid systems.

A Control System for a High-Quality Generating Set Equipped With a Two-Shaft Gas Turbine

1991 ◽  
Vol 113 (2) ◽  
pp. 290-295 ◽  
Author(s):  
H. Kumakura ◽  
T. Matsumura ◽  
E. Tsuruta ◽  
A. Watanabe
Keyword(s):  
Control System ◽  
Gas Turbine ◽  
Gas Turbines ◽  
High Quality ◽  
Constant Frequency ◽  
Generating Set ◽  
Generating Sets ◽  
Power Turbine ◽  
Computer Centers ◽  
Supply Systems

A control system has been developed for a high-quality generating set (150-kW) equipped with a two-shaft gas turbine featuring a variable power turbine nozzle. Because this generating set satisfies stringent frequency stability requirements, it can be employed as the direct electric power source for computer centers without using constant-voltage, constant-frequency power supply systems. Conventional generating sets of this kind have normally been powered by single-shaft gas turbines, which have a larger output shaft inertia than the two-shaft version. Good frequency characteristics have also been realized with the two-shaft gas turbine, which provides superior quick start ability and lower fuel consumption under partial loads.

NMHC and VOC Speciation of the Exhaust Gas From a Gas Turbine Engine Using Alternative, Renewable and Conventional Jet A-1 Aviation Fuels

2014 ◽  
Author(s):  
Mohamed A. Altaher ◽  
Hu Li ◽  
Simon Blakey ◽  
Winson Chung
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Aviation Fuel ◽  
Exhaust Gas ◽  
Turbine Engine ◽  
Fuel Blends ◽  
Auxiliary Power ◽  
Unburned Hydrocarbons ◽  
Full Power ◽  
Two Stages

This paper investigated the emissions of individual unburned hydrocarbons and carbonyl compounds from the exhaust gas of an APU (Auxiliary Power Unit) gas turbine engine burning various fuels. The engine was a single spool, two stages of turbines and one stage of centrifugal compressor gas turbine engine, and operated at idle and full power respectively. Four alternative aviation fuel blends with Jet A-1 were tested including GTL, hydrogenated renewable jet fuel and fatty acid ester. C2-C4 alkenes, benzene, toluene, xylene, trimethylbenzene, naphthalene, formaldehyde, acetaldehyde and acrolein emissions were measured. The results show at the full power condition, the concentrations for all hydrocarbons were very low (near or below the instrument detection limits). Formaldehyde was a major aldehyde species emitted with a fraction of around 60% of total measured aldehydes emissions. Formaldehydes emissions were reduced for all fuels compared to Jet A-1 especially at the idle conditions. There were no differences in acetaldehydes and acrolein emissions for all fuels; however, there was a noticeable reduction with GTL fuel. The aromatic hydrocarbon emissions including benzene and toluene are decreased for the alternative and renewable fuels.

Development and Fabrication of Silicon Nitride Components for Ceramic Gas Turbine

1997 ◽  
Author(s):  
Keisuke Makino ◽  
Ken-Ichi Mizuno ◽  
Toru Shimamori
Keyword(s):  
High Temperature ◽  
Silicon Nitride ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Turbine Blades ◽  
High Strength ◽  
Inlet Temperature ◽  
Turbine Inlet Temperature ◽  
Spark Plug ◽  
Power Turbine

NGK Spark Plug Co., Ltd. has been developing various silicon nitride materials, and the technology for fabricating components for ceramic gas turbines (CGT) using theses materials. We are supplying silicon nitride material components for the project to develop 300 kW class CGT for co-generation in Japan. EC-152 was developed for components that require high strength at high temperature, such as turbine blades and turbine nozzles. In order to adapt the increasing of the turbine inlet temperature (TIT) up to 1,350 °C in accordance with the project goals, we developed two silicon nitride materials with further unproved properties: ST-1 and ST-2. ST-1 has a higher strength than EC-152 and is suitable for first stage turbine blades and power turbine blades. ST-2 has higher oxidation resistance than EC-152 and is suitable for power turbine nozzles. In this paper, we report on the properties of these materials, and present the results of evaluations of these materials when they are actually used for CGT components such as first stage turbine blades and power turbine nozzles.

Problems in the Mechanical Design of Gas Turbines

1947 ◽  
Vol 14 (2) ◽  
pp. A99-A102
Author(s):  
Ronald B. Smith
Keyword(s):  
Gas Turbine ◽  
High Temperatures ◽  
Gas Turbines ◽  
Mechanical Design

Abstract High temperatures involved in the operation of the gas turbine have introduced many new problems in the properties of the metals with which the designer has to work. This paper outlines some of these and offers a line of approach taken successfully by the author’s company in solving them.

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