Design of a Pulsing Flow Driven Turbine

2020 ◽  
Author(s):  
Mark H. Fernelius ◽  
Steven E. Gorrell
Keyword(s):  
Gas Turbine ◽  
Entropy Generation ◽  
Leading Edge ◽  
Turbine Engine ◽  
Turbine Efficiency ◽  
Pressure Gain Combustion ◽  
Inlet Conditions ◽  
Pulsing Flow ◽  
Dynamics Simulations ◽  
Turbine Design

Abstract There is widespread interest in using pressure gain combustion in gas turbine engines to increase gas turbine engine efficiency and reduce fuel consumption. However, the fluctuating turbine inlet conditions inherent with pressure gain combustion cause a decrease in turbine efficiency. Designing a turbine for pulsing flow would counteract these losses. An optimization of turbine geometry for pulsing flow was conducted with entropy generation as the objective function. A surrogate model was used for the optimizations based on data extracted from 2D computational fluid dynamics simulations. Optimizations run for different pulsing amplitudes informed a revised turbine design. The new turbine geometry was validated with a periodic, time-accurate simulation and a decrease in entropy generation of 35% was demonstrated. The design recommendations were to weight the design of the turbine toward the peak of the pressure pulse, to consider the range of inlet angles and decrease the camber near the leading edge, and to reduce the blade turning.

Predicting Efficiency of a Turbine Driven by Pulsing Flow

2017 ◽  
Author(s):  
Mark H. Fernelius ◽  
Steven E. Gorrell
Keyword(s):  
Computational Fluid Dynamic ◽  
Fluid Dynamic ◽  
Pulse Amplitude ◽  
Driving Factor ◽  
Dynamic Simulations ◽  
Turbine Engine ◽  
Turbine Efficiency ◽  
Pressure Gain Combustion ◽  
Pulsing Flow ◽  
Flow Experiences

One of the challenges of integrating pressure gain combustion into a gas turbine engine is that a turbine driven by pulsing flow experiences a decrease in efficiency. Computational fluid dynamic simulations validated with experiments showed that pulse amplitude is the driving factor for decreased turbine efficiency and not the pulsing frequency. A quadratic correlation between turbine efficiency and corrected pulse amplitude is presented. Incidence variation is shown to cause the change in turbine efficiency and a correlation between corrected incidence and corrected amplitude is shown to predict turbine efficiency.

Simple Instrumentation Rake Designs for Gas Turbine Engine Testing

1996 ◽  
Author(s):  
Peter D. Smout ◽  
Steven C. Cook
Keyword(s):  
Gas Turbine ◽  
Mechanical Damage ◽  
Engine Performance ◽  
Leading Edge ◽  
Gas Turbine Engine ◽  
Calibration Data ◽  
Turbine Engine ◽  
Industry Standard ◽  
Repair Costs ◽  
Engine Testing

The determination of gas turbine engine performance relies heavily on intrusive rakes of pilot tubes and thermocouples for gas path pressure and temperature measurement. For over forty years, Kiel-shrouds mounted on the rake body leading edge have been used as the industry standard to de-sensitise the instrument to variations in flow incidence and velocity. This results in a complex rake design which is expensive to manufacture, susceptible to mechanical damage, and difficult to repair. This paper describes an exercise aimed at radically reducing rake manufacture and repair costs. A novel ’common cavity rake’ (CCR) design is presented where the pressure and/or temperature sensors are housed in a single slot let into the rake leading edge. Aerodynamic calibration data is included to show that the performance of the CCR design under uniform flow conditions and in an imposed total pressure gradient is equivalent to that of a conventional Kiel-shrouded rake.

Parameter Optimization on Combined Gas Turbine-Fuel Cell Power Plants

2005 ◽  
Vol 2 (4) ◽  
pp. 268-273 ◽  
Author(s):  
Rainer Kurz
Keyword(s):  
Fuel Cell ◽  
Gas Turbine ◽  
Power Plants ◽  
Pressure Ratio ◽  
Design Parameters ◽  
Turbine Efficiency ◽  
Compressor Pressure Ratio ◽  
Turbine Design ◽  
Cycle Efficiency ◽  
Compressor Efficiency

A thermodynamic model for a gas turbine-fuel cell hybrid is created and described in the paper. The effects of gas turbine design parameters such as compressor pressure ratio, compressor efficiency, turbine efficiency, and mass flow are considered. The model allows to simulate the effects of fuel cell design parameters such as operating temperature, pressure, fuel utilization, and current density on the cycle efficiency. This paper discusses, based on a parametric study, optimum design parameters for a hybrid gas turbine. Because it is desirable to use existing gas turbine designs for the hybrids, the requirements for this hybridization are considered. Based on performance data for a typical 1600hp industrial single shaft gas turbine, a model to predict the off-design performance is developed. In the paper, two complementary studies are performed: The first study attempts to determine the range of cycle parameters that will lead to a reasonable cycle efficiency. Next, an existing gas turbine, that fits into the previously established range of parameters, will be studied in more detail. Conclusions from this paper include the feasibility of using existing gas turbine designs for the proposed cycle.

Conversion of the AE 1107C From the V-22 Osprey Application to Marine Service

2013 ◽  
Author(s):  
Zechariah D. Green ◽  
Sean Padfield ◽  
Andrew F. Barrett ◽  
Paul G. Jones
Keyword(s):  
Gas Turbine ◽  
System Integration ◽  
Development Program ◽  
Gas Turbine Engine ◽  
Naval Vessel ◽  
Turbine Engine ◽  
The Us ◽  
Technical Risk ◽  
Turbine Design ◽  
System Designs

This paper presents a study on the conversion of the Rolls-Royce AE 1107C V-22 Osprey gas turbine engine into the MT7 Ship-to-Shore Connector (SSC) marine gas turbine engine. The US Navy led SSC design requires a propulsion and lift gas turbine rated at 5,230 shaft horsepower, which the AE 1107C variant MT7 is capable of providing with margin on power and specific fuel consumption. The MT7 leverages the AE family of engines to provide a propulsion and lift engine solution for the SSC craft. Extensive testing and analysis completed during the AE 1107C development program aided in the robust gas turbine design required to meet the needs of the SSC program. Requirements not met by the AE 1107C configuration were achieved with designs based on the AE family of engines and marine grade sub-system designs. Despite the fact that system integration and testing remain as key activities for integrating the MT7 with the SSC craft, conversion of the AE 1107C FAA certified engine into an American Bureau of Shipping Naval Vessel Rules Type Approved MT7 engine provides a low technical risk alternative for the demanding requirements of the SSC application.

Centenary of the First Gas Turbine to Give Net Power Output: A Tribute to Ægidius Elling

2004 ◽  
Author(s):  
Lars E. Bakken ◽  
Kristin Jordal ◽  
Elisabet Syverud ◽  
Timot Veer
Keyword(s):  
Gas Turbine ◽  
Power Output ◽  
Water Injection ◽  
Power Delivery ◽  
Compressed Air ◽  
Turbine Engine ◽  
Power Turbine ◽  
Clear Vision ◽  
Turbine Design ◽  
Net Power Output

The paper presents the work of the Norwegian engineer Ægidius Elling (ref. Figure 1), from his gas turbine patent in 1884 to the first gas turbine in the world producing net power in 1903. It traces the subsequent patents, until his final experiments in 1932. Focus is placed on an engineer with a clear vision of the potential of the gas turbine engine and the capability to realize his ideas, in spite of the lack of industrial financial support. In 1903, Elling noted in his diary that he thought he had built and operated the first gas turbine that could give net power delivery. The power delivery of this very first gas turbine was extracted as compressed air. The net power delivery was modest, only the equivalent of 11 hp. The reason for producing air was the accelerating use of pneumatic tools. Refinements to the gas turbine design soon followed, such as water injection for compressor cooling and recuperation of exhaust gas heat. In 1904, the power output of Elling’s gas turbine had increased to 44 hp. Elling also abandoned the production of compressed air in favor of electric power generation. In a patent from 1923, Elling described a multi-shaft engine with intercooling and reheat, with an independent power turbine. He improved this gas turbine in the period up to 1932, when the engine reached a power output of approximately 75 hp. In 1933, Elling wrote prophetically, “When I started to work on the gas turbine in 1882 it was for the sake of aeronautics and I firmly believe that aeronautics is still waiting for the gas turbine.” Unfortunately, Elling was never to take part in this development, although he pursued his work on the gas turbine until his death in 1949.

Gas Turbine With Intermediate Heat Exchanger for Flight Application

1990 ◽  
Author(s):  
J. Shapiro ◽  
A. Levy
Keyword(s):  
Heat Exchanger ◽  
Gas Turbine ◽  
High Power ◽  
Fuel Economy ◽  
Weight Ratio ◽  
Power Weight ◽  
Turbine Engine ◽  
Additional Weight ◽  
Intermediate Heat Exchanger ◽  
Turbine Design

High power/weight ratio and low SFC are the most important requirements for an airborne engine. This may be achieved by a gas turbine engine with an intermediate heat exchanger, combined with a double-decked compressor-turbine design. In this engine, the specific fuel consumption is minimal at 70% of maximum power output for best fuel economy in helicopter engines. The additional weight, due to its design, is compensated by fuel saved in less than one hour flight for a 926 kW cruise power engine.

scholarly journals An Empirically-Based Simulation Model for Heavy-Duty Gas Turbine Engines Using Treated Residual Fuel

1982 ◽  
Author(s):  
J. C. Blanton ◽  
W. F. O’Brien
Keyword(s):  
Simulation Model ◽  
Gas Turbine ◽  
Combustion Products ◽  
Heavy Duty ◽  
Turbine Engine ◽  
Engine Simulation ◽  
Turbine Efficiency ◽  
Rate Of Increase ◽  
Ash Deposit ◽  
Heavy Duty Gas Turbine

An empirically-based engine simulation model was developed to analyze the operation of a heavy-duty gas turbine on ash-bearing fuel. The effect of the ash in the combustion products on turbine efficiency was determined employing field data. The model was applied to the prediction of the performance of an advanced-cooled turbine engine with a water-cooled first-stage nozzle, when operated with ash-bearing fuels. Experimental data from a turbine simulator rig were used to estimate the expected rates of ash deposit formation in the advanced-cooled turbine engine, so that the results could be compared with those for current engines. The results of the simulations indicate that the rate of decrease in engine power would be 32 percent less in the advanced-cooled engine with water cooling. An improvement in predicted specific fuel consumption performance was also noted, with a rate of increase of 38 percent for the advanced-cooled engine.

Mapping Efficiency of a Pulsing Flow-Driven Turbine

2020 ◽  
Vol 142 (6) ◽  
Author(s):  
Mark H. Fernelius ◽  
Steven E. Gorrell
Keyword(s):  
Pressure Pulse ◽  
Pressure Ratio ◽  
Pulse Amplitude ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Turbine Efficiency ◽  
Pressure Gain Combustion ◽  
Pulsing Flow ◽  
Cycle Efficiency ◽  
Flow Experiences

Abstract Pressure gain combustion (PGC) shows potential to increase the cycle efficiency of conventional gas turbine engines (GTEs) if used in place of the steady combustor. However, a turbine driven by pulsing flow experiences a decrease in efficiency. An experimental rig was built to compare a steady flow-driven turbine with a pulsing flow-driven turbine. The pressure pulse was a full annular, sinusoidal pressure pulse. The experimental data showed a decrease in turbine efficiency and pressure ratio. The pressure pulse amplitude and not the frequency was discovered to be the cause for the decrease in turbine efficiency for the current experimental setup. The decrease in turbine efficiency was mapped with turbine pressure ratio and corrected amplitude to demonstrate how the efficiency of a turbine under pulsing flow conditions could be mapped.

scholarly journals Low Cost Short Life Gas Turbine Design

1971 ◽  
Author(s):  
D. L. Murray ◽  
W. E. Kidd
Keyword(s):  
Gas Turbine ◽  
Low Cost ◽  
Innovative Design ◽  
Design Studies ◽  
Turbine Engine ◽  
Engine Design ◽  
Control Concept ◽  
System Requirements ◽  
Turbine Design ◽  
Accessory Problem

Results of low cost gas turbine engine design studies are presented. System requirements are discussed and their effects on engine design and cost are analyzed. Parametric performance data are presented and the use of these data in engine build cost trades is discussed. The evolution of specific component fabrication techniques on selected components is discussed, and the overall effect on the engine cost is analyzed and described. The technique of achieving low manufacturing costs by the use of innovative design, keyed to operational requirements rather than new processes, is described. The accessory problem is discussed and a potentially low cost fuel control concept described. A cross section drawing of a simple production turbojet is shown and the use of a technique for low cost design is outlined.

An Empirically Based Simulation Model for Heavy-Duty Gas Turbine Engines Using Treated Residual Fuel

1983 ◽  
Vol 105 (1) ◽  
pp. 167-171
Author(s):  
J. C. Blanton ◽  
W. F. O’Brien
Keyword(s):  
Simulation Model ◽  
Gas Turbine ◽  
Combustion Products ◽  
Heavy Duty ◽  
Turbine Engine ◽  
Engine Simulation ◽  
Turbine Efficiency ◽  
Rate Of Increase ◽  
Ash Deposit ◽  
Heavy Duty Gas Turbine

An empirically based engine simulation model was developed to analyze the operation of a heavy-duty gas turbine on ash-bearing fuel. The effect of the ash in the combustion products on turbine efficiency was determined employing field data. The model was applied to the prediction of the performance of an advanced-cooled turbine engine with a water-cooled first-stage nozzle, when operated with ash-bearing fuels. Experimental data from a turbine simulator rig were used to estimate the expected rates of ash deposit formation in the advanced-cooled turbine engine, so that the results could be compared with those for current engines. The results of the simulations indicate that the rate of decrease in engine power would be 32 percent less in the advanced-cooled engine with water cooling. An improvement in predicted specific fuel consumption performance was also noted, with a rate of increase of 38 percent for the advanced-cooled engine.

Sign in / Sign up

Export Citation Format

Share Document