scholarly journals Design and Test of a New Axial Compressor for the Nuovo Pignone Heavy Duty Gas Turbines

1996 ◽  
Author(s):  
Erio Benvenuti
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Dynamic Pressure ◽  
Pressure Ratio ◽  
Axial Compressor ◽  
Leading Edge ◽  
Meridional Flow ◽  
Heavy Duty ◽  
Pressure Transducers ◽  
Easy Integration

This axial compressor design was primarily focused to increase the power rating of the current Nuovo Pignone PGT10 Heavy-Duty gas turbine by 10%. In addition, the new 11-stage design favourably compares with the existing 17-stage compressor in terms of simplicity and cost. By seating the flowpath and blade geometry, the new aerodynamic design can be applied to gas turbines with different power ratings as well. The reduction in the stage number was achieved primarily through the meridional flow-path redesign. The resulting higher blade peripheral speeds achieve larger stage pressure ratios without increasing the aerodynamic loadings. Wide chord blades keep the overall length unchanged thus assuring easy integration with other existing components. The compressor performance map was extensively checked over the speed range required for two-shaft gas turbines. The prototype unit was installed on a special PGT10 gas turbine setup, that permitted the control of pressure ratio independently from the turbine matching requirements. The flowpath instrumentation included strain-gages, dynamic pressure transducers and stator vane leading edge aerodynamic probes to determine individual stage characteristics. The general blading vibratory behavior was proved fully satisfactory. With minor adjustments to the variable stator settings the front stage aerodynamic matching was optimized and the design performance was achieved.

Design and Test of a New Axial Compressor for the Nuovo Pignone Heavy-Duty Gas Turbines

1997 ◽  
Vol 119 (3) ◽  
pp. 633-639 ◽  
Author(s):  
Erio Benvenuti
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Dynamic Pressure ◽  
Pressure Ratio ◽  
Axial Compressor ◽  
Leading Edge ◽  
Heavy Duty ◽  
Pressure Transducers ◽  
Heavy Duty Gas Turbine ◽  
Easy Integration

This axial compressor design was primarily focused to increase the power rating of the current Nuovo Pignone PGT10 Heavy-Duty gas turbine by 10 percent. In addition, the new 11-stage design favorably compares with the existing 17-stage compressor in terms of simplicity and cost. By scaling the flowpath and blade geometry, the new aerodynamic design can be applied to gas turbines with different power ratings as well. The reduction in the stage number was achieved primarily through the meridional flowpath redesign. The resulting higher blade peripheral speeds achieve larger stage pressure ratios without increasing the aerodynamic loadings. Wide chord blades keep the overall length unchanged thus assuring easy integration with other existing components. The compressor performance map was extensively checked over the speed range required for two-shaft gas turbines. The prototype unit was installed on a special PGT10 gas turbine setup, that permitted the control of pressure ratio independently from the turbine matching requirements. The flowpath instrumentation included strain gages, dynamic pressure transducers, and stator vane leading edge aerodynamic probes to determine individual stage characteristics. The general blading vibratory behavior was proved fully satisfactory. With minor adjustments to the variable stator settings, the front stage aerodynamic matching was optimized and the design performance was achieved.

CTV: A New Method for Mapping a Full Scale Prototype of an Axial Compressor

1996 ◽  
Author(s):  
Vasco Mezzedimi ◽  
Pierluigi Nava ◽  
Dave Hamilla
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Theoretical Basis ◽  
Axial Compressor ◽  
Heavy Duty ◽  
Test Vehicle ◽  
Testing Method ◽  
Area Reduction ◽  
Speed Range ◽  
Compressor Inlet

The full mapping of a new gas turbine axial compressor at different speeds, IGV settings and pressure ratios (from choking to surge) has been performed utilizing a complete gas turbine with a suitable set of modifications. The main additions and modifications, necessary to transform the turbine into the Compressor Test Vehicle (CTV), are: - Compressor inlet throttling valve addition - Compressor discharge bleed valve addition - Turbine 1st stage nozzle area reduction - Starting engine change (increase in output and speed range). This method has been successfully employed on two different single shaft heavy-duty gas turbines (with a power rating of 11MW and 170 MW respectively). The paper describes the theoretical basis of this testing method and a specific application with the above mentioned 170 MW machine.

Dry, Low Emissions for the ‘H’ Heavy-Duty Industrial Gas Turbines: Full-Scale Combustion System Rig Test Results

2003 ◽  
Author(s):  
Geoff Myers ◽  
Dan Tegel ◽  
Markus Feigl ◽  
Fred Setzer ◽  
William Bechtel ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Pressure Ratio ◽  
Combined Cycle ◽  
Full Scale ◽  
Combustion System ◽  
Heavy Duty ◽  
Test Program ◽  
Industrial Gas Turbines ◽  
Inlet Conditions

The lean, premixed DLN2.5H combustion system was designed to deliver low NOx emissions from 50% to 100% load in both the Frame 7H (60 Hz) and Frame 9H (50 Hz) heavy-duty industrial gas turbines. The H machines employ steam cooling in the gas turbine, a 23:1 pressure ratio, and are fired at 1440 C (2600 F) to deliver over-all thermal efficiency for the combined-cycle system near 60%. The DLN2.5H combustor is a modular can-type design, with 14 identical chambers used on the 9H machine, and 12 used on the smaller 7H. On a 9H combined-cycle power plant, both the gas turbine and steam turbine are fired using the 14-chamber DLN2.5H combustion system. An extensive full-scale, full-pressure rig test program developed the fuel-staged dry, low emissions combustion system over a period of more than five years. Rig testing required test stand inlet conditions of over 50 kg/s at 500 C and 28 bar, while firing at up to 1440 C, to simulate combustor operation at base load. The combustion test rig simulated gas path geometry from the discharge of the annular tri-passage diffuser through the can-type combustion liner and transition piece, to the inlet of the first stage turbine nozzle. The present paper describes the combustion system, and reports emissions performance and operability results over the gas turbine load and ambient temperature operating range, as measured during the rig test program.

Axial Compressor Degradation Effects on Heavy Duty Gas Turbines Overall Performances

2013 ◽  
Author(s):  
Pio Astrua ◽  
Stefano Cecchi ◽  
Stefano Piola ◽  
Andrea Silingardi ◽  
Federico Bonzani
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Axial Compressor ◽  
Performance Parameters ◽  
Heavy Duty ◽  
Compressor Blades ◽  
Modular Model ◽  
Secondary Air ◽  
The Impact ◽  
Insight Into

The operation of a gas turbine is the result of the aero-thermodynamic matching of several components which necessarily experience aging and degradation over time. An approach to treat degradation phenomena of the axial compressor is provided, with an insight into the impact they have on compressor operation and on overall GT performances. The analysis is focused on the surface fouling of compressor blades and on rotor tip clearances variation. A modular model is used to simulate the gas turbine operation in design and off-design conditions and the aerodynamic impact of fouling and rotor tip clearances increase is assessed by means of dedicated loss and deviation correlations implemented in the 1D mid-streamline code of the compressor modules. The two different degradation sources are individually considered and besides the overall GT performance parameters, the analysis includes an evaluation of the compressor degradation impact on the secondary air system.

scholarly journals Development of a High Pressure Ratio Centrifugal Compressor for 300kW-Class Ceramic Gas Turbine

1997 ◽  
Author(s):  
T. Sakai ◽  
Y. Tohbe ◽  
T. Fujii ◽  
T. Tatsumi
Keyword(s):  
Research And Development ◽  
Gas Turbine ◽  
Gas Turbines ◽  
High Efficiency ◽  
Pressure Ratio ◽  
Flow Distribution ◽  
Leading Edge ◽  
Inlet Temperature ◽  
Angle Distribution ◽  
Gas Generator

Research and development of ceramic gas turbines (CGT), which is promoted by the Japanese Ministry of International Trade and Industry (MITI), was started in 1988. The target of the CGT project is development of a 300kW-class ceramic gas turbine with a 42 % thermal efficiency and a turbine inlet temperature (TIT) of 1350°C. Two types of CGT engines are developed in this project. One of the CGT engines, which is called CGT302, is a recuperated two-shaft gas turbine with a compressor, a gas-generator turbine, and a power turbine for cogeneration. In this paper, we describe the research and development of a compressor for the CGT302. Specification of this compressor is 0.89 kg/sec air flow rate and 8:1 pressure ratio. The intermediary target efficiency is 78% and the final target efficiency is 82%, which is the highest level in email centrifugal compressors like this one. We measured impeller inlet and exit flow distribution using three-hole yaw probes which were traversed from the shroud to the hub. Based on the measurement of the impeller exit flow, diffusers with a leading edge angle distribution adjusted to the inflow angle were designed and manufactured. Using this diffuser, we were able to attain a high efficiency (8:1 pressure ratio and 78% adiabatic efficiency).

The Evolution of Compressor and Turbine Bladings in Gas Turbine Design

1967 ◽  
Vol 89 (2) ◽  
pp. 199-205 ◽  
Author(s):  
C. Seippel
Keyword(s):  
Steam Turbine ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Pressure Ratio ◽  
Parallel Evolution ◽  
Axial Compressor ◽  
Expansion Turbine ◽  
The Stability ◽  
Turbine Design ◽  
The City

The author, having been associated with the construction of gas turbines from the first 4000-kw unit delivered in 1939 to the city of Neuchaˆtel to the present time, gives some personal views on the evolution of the axial compressor and turbine bladings which are the key elements to the gas turbines. The axial compressor was created to supply air efficiently for the supercharged “Velox” boiler. It made the evolution to the modern gas turbine possible. The main problems encountered were related to the stability of flow. An enormous increase of volume capacity was achieved in the course of time. The increase of pressure ratio made special measures necessary to overcome instability at starting. The expansion turbine started on the basis of steam turbine practice and underwent a parallel evolution to large capacities. Its particular problems are related to the high temperatures of the gases.

Flexible Spacers Compressor Stator Blades for Heavy Industrial Gas Turbines Model 7EA

2003 ◽  
Author(s):  
Steve Ingistov
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Field Experience ◽  
Axial Compressor ◽  
Heavy Duty ◽  
Combustion Gas ◽  
Mechanical Integrity ◽  
Industrial Gas Turbines ◽  
Last Stage

This paper describes efforts to upgrade the mechanical integrity of axial compressor stator blades. The blades under discussion are part of an axial compressor of a heavy duty industrial Combustion Gas Turbine (CGT) made by GE, frame No. 7, model EA. The axial compressor stator blades, in the later stages of compression, are kept in required position by spacers or shims shaped to match the root profile of the blades. These spacers/shims may be as thick as 1/4 of an inch and as thin as 1/32 of an inch. These spacers/shims tend to wiggle out of the slots and eventually liberate themselves from the stator. This paper introduces a proposed solution to minimize liberation of the spacer/shims by introduction of flexible spacers/shims. This paper also describes field experience with loss of the stator blades in the last stage of compression, due to aerodynamic disturbances.

scholarly journals The PGT 10 Heavy Duty 10 MW Gas Turbine

1988 ◽  
Author(s):  
R. Gusso ◽  
E. Benvenuti ◽  
D. Bianchi ◽  
D. Sabella
Keyword(s):  
Gas Turbine ◽  
High Reliability ◽  
Pressure Ratio ◽  
Axial Compressor ◽  
Load Testing ◽  
Heavy Duty ◽  
Heavy Duty Gas Turbine ◽  
Performance Results ◽  
Turbine Design ◽  
Industrial Gas Turbine

The PGT 10 two-shaft, 10 MW, industrial gas turbine has a capability of up to 34% simple-cycle efficiency, high reliability with extended range of operation and low exhaust emissions. Features like the 14:1 pressure ratio and high specific mass flow transonic axial compressor are at the highest levels in the heavy-duty gas turbine design. The firing temperature, the blade cooling techniques, the extended modularization of components and subassemblies are in their turn representative of the well-proven, state-of-art technology: performance results also from the aero-thermodynamic design aimed at maximizing component efficiencies. This paper introduces the major aspects of the PTG 10 turbine design. After full-load testing was successfully completed on the first units, the PTG 10 has entered normal production in 1987 and several units have already been installed or shipped.

Unsteady Operative Conditions of Bleeding Lines in Heavy Duty Axial Gas Turbine

2015 ◽  
Author(s):  
Marco Cioffi
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Flow Behavior ◽  
Axial Compressor ◽  
Heavy Duty ◽  
Fast Evaluation ◽  
Axial Compressors ◽  
Proper Design ◽  
Valve Opening ◽  
Start Ups

The proper design and operation of air bleeding pipes (blow-off lines) from axial compressors in heavy duty gas turbines is relevant to protect the compressor during start-ups and shut-downs by avoiding dangerous flow instabilities in the first stages. The blow-off lines are usually equipped by valves, which are closed during normal gas turbine operation and opened at low rotor speed. During gas turbine shut-downs the blow-off valves open instantaneously. In this paper the unsteady flow behavior in blow-off lines following the valve opening is presented together with numerical results based on available field data. The paper main scope is to address and to help the design of experimental activities on production gas turbines and to make available some simple numerical tools to be adopted during the industrial design of an axial compressor and its auxiliary systems. The performed analysis results have been used to define the structural requirements and the correct positioning of the measuring probes installed in blow-off lines. In addition the presented models are part of the compressor design loop, used to compute a fast evaluation of the limiting mass flow rate, which characterizes the blow-off pipes as gas turbine safety devices.

Development and Validation of a Model for Axial Compressor Fouling Simulation

2010 ◽  
Author(s):  
F. Melino ◽  
A. Peretto ◽  
P. R. Spina
Keyword(s):  
Gas Turbine ◽  
Power Output ◽  
Gas Turbines ◽  
Pressure Ratio ◽  
Axial Compressor ◽  
Computer Code ◽  
Performance Curves ◽  
Compressor Inlet ◽  
Compressor Performance ◽  
Development And Validation

Gas turbine axial compressor performance are heavily influenced by blade fouling; as a result, the gas turbines efficiency and producible power output decrease. In this study a model, able to evaluate the performance degradation of an axial compressor due to fouling, is developed and validated. The model is validated against experimental results available in literature and included into a computer code developed by the Authors (IN.FO.G.T.E) which is able to estimate the performance of every commercial gas turbine by using a stage stacking methods for the simulation of compressor behavior. The goal of this study is to show and discuss the change in gas turbine main performance (such as efficiency, power output, compressor inlet mass flow rate, pressure ratio) due to compressor fouling and also highlight and discuss the change in compressor stages performance curves.

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