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.

scholarly journals The Part-Load Performance of a Gas Turbine Engine With Two Turbines Working in Parallel

1986 ◽  
Author(s):  
Yousef S. H. Najjar ◽  
Taha K. Aldoss
Keyword(s):  
Gas Turbine ◽  
Power Output ◽  
Pressure Ratio ◽  
Gas Turbine Engine ◽  
Inlet Temperature ◽  
Combustion Chambers ◽  
Turbine Engine ◽  
Combustion Gases ◽  
Power Turbine ◽  
In Series

To reduce the inefficiency and the drawbacks incurred by reheat in a gas turbine engine with the two turbines in series, a parallel arrangement is investigated. The combustion gases expand to atmospheric pressure in each turbine. One of the turbines drives the compressor to which it is mechanically coupled while the other develops the power output of the plant. Two methods of control for the reduction of power are considered: a) Varying the fuel supply to the combustion chambers so that the inlet temperature to the turbine driving the compressor is constant, while the inlet temperature to the power turbine is reduced. b) Reducing both temperatures while keeping them equal. The effects of turbines inlet temperatures, pressure ratio and pressure loss in combustion chambers on the cycle efficiency and power output are studied and a sensitivity analysis is carried out, with the aid of a specially constructed computer program. The first method of control proved to be superior.

Analytical efficiency comparison between gas turbine and gas turbine hybrid engines for passenger cars

1997 ◽  
Vol 211 (2) ◽  
pp. 113-119 ◽  
Author(s):  
W Cheng ◽  
D. G. Wilson ◽  
A. C. Pfahnl
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Passenger Cars ◽  
Long Distance ◽  
Vehicle Performance ◽  
Turbine Engine ◽  
Compression Ignition Engines ◽  
Power Turbine ◽  
Performance And Emissions ◽  
Efficiency Comparison

The performance and emissions of two alternative types of gas turbine engine for a chosen family vehicle are compared. One engine is a regenerative 71 kW gas turbine; the other is a hybrid power plant composed of a 15 kW gas turbine and a 7 MJ flywheel. These engines would give generally similar vehicle performance to that produced by 71 kW spark ignition and compression ignition engines. (The turbine engines would be lighter and, with a free power turbine, would have a more favourable torque-speed curve (1), giving them some advantages.) Results predict that for long-distance trips the hybrid engine would have a considerably better fuel economy and would produce lower emissions than the piston engines, and that the ‘straight’ gas turbine would be even better. For shorter commuting trips the hybrid would be able to run entirely from energy acquired and stored from house electricity, and it could therefore be the preferred choice for automobiles used primarily for urban driving when environmental factors are taken into account. However, the degradation of remaining energy in flywheel batteries and thermal energy in the regenerator and other engine hot parts between use periods will result in more energy being used than for the straight gas turbine engine using normal liquid fuel. The higher initial cost and greater complexity of the hybrid engine will be additional disadvantages.

Comparative Analysis of Different Inlet Air Cooling Technologies Including Solar Energy to Boost Gas Turbine Combined Cycles in Hot Regions

2018 ◽  
Vol 140 (11) ◽  
Author(s):  
Ahmed Abdel Rahman ◽  
Esmail M. A. Mokheimer
Keyword(s):  
Comparative Analysis ◽  
Gas Turbine ◽  
Output Power ◽  
Power Output ◽  
Combined Cycle ◽  
Air Cooling ◽  
Absorption Chiller ◽  
Absorption Chillers ◽  
Combined Cycles ◽  
Net Power Output

Cooling the air before entering the compressor of a gas turbine of combined cycle power plants is an effective method to boost the output power of the combined cycles in hot regions. This paper presents a comparative analysis for the effect of different air cooling technologies on increasing the output power of a combined cycle. It also presents a novel system of cooling the gas turbine inlet air using a solar-assisted absorption chiller. The effect of ambient air temperature and relative humidity on the output power is investigated and reported. The study revealed that at the design hour under the hot weather conditions, the total net power output of the plant drops from 268 MW to 226 MW at 48 °C (15.5% drop). The increase in the power output using fogging and evaporative cooling is less than that obtained with chillers since their ability to cool down the air is limited by the wet-bulb temperature. Integrating conventional and solar-assisted absorption chillers increased the net power output of the combined cycle by about 35 MW and 38 MW, respectively. Average and hourly performance during typical days have been conducted and presented. The plants without air inlet cooling system show higher carbon emissions (0.73 kg CO2/kWh) compared to the plant integrated with conventional and solar-assisted absorption chillers (0.509 kg CO2/kWh) and (0.508 kg CO2/kWh), respectively. Also, integrating a conventional absorption chiller shows the lowest capital cost and levelized electricity cost (LEC).

GRIFFIN VENTURE GAS TURBINE FAILURE 1997

1999 ◽  
Vol 39 (1) ◽  
pp. 532
Author(s):  
K.R. Black
Keyword(s):  
Gas Turbine ◽  
Detection System ◽  
Short Circuit ◽  
Fire Detection ◽  
Turbine Engine ◽  
Fire Extinguishing ◽  
Power Turbine ◽  
Engine Failure ◽  
As Stress ◽  
Safety Systems

On 10 November 1997 the BHP Petroleum-operated Floating Production, Storage and Offloading (FPSO) crude oil facility the Griffin Venture suffered an unprecedented mechanical failure of a gas turbine engine. The power turbine casing was breached resulting in an explosion and fire within the engine room space. The incident was safely controlled without personnel injury in what was a world class emergency response effort.The engine failure was caused by an unusual form of crack propagation known as stress assisted grain boundary oxidation (SAGBO) of the engine's high pressure power turbine disc. The incident also identified a number of safety system improvements, many of which could be applicable to other facilities. These included smoke impairment of the accommodation (designated temporary safe refuge) because of leaking fire doors, failure to release the engine package fire extinguishing system and failure of the fire detection system due to short circuit intolerance nine minutes after the incident commenced.The facility was repaired in Singapore by Sembawang Shipyard where new engine cores were fitted and many of the safety systems were upgraded. Production resumed in March 1998 since when the Griffin Venture has produced above target oil volumes and record gas volumes.

Application of a Miniature Telemetry System in a Small Gas Turbine Engine

2011 ◽  
Author(s):  
Stephen A. Long ◽  
Patrick A. Reiger ◽  
Michael W. Elliott ◽  
Stephen L. Edney ◽  
Frank Knabe ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Cooling System ◽  
Turbine Rotor ◽  
Gas Turbine Engine ◽  
Telemetry System ◽  
Strain Gages ◽  
Turbine Engine ◽  
Power Turbine ◽  
Successful Execution ◽  
Integration Effort

For the purpose of assessing combustion effects in a small gas turbine engine, there was a requirement to evaluate the rotating temperature and dynamic characteristics of the power turbine rotor module. This assessment required measurements be taken within the engine, during operation up to maximum power, using rotor mounted thermocouples and strain gages. The acquisition of this data necessitated the use of a telemetry system that could be integrated into the existing engine architecture without affecting performance. Due to space constraints, housing of the telemetry module was limited to placement in a hot section. In order to tolerate the high temperature environment, a cooling system was developed as part of the integration effort to maintain telemetry module temperatures within the limit allowed by the electronics. Finite element thermal analysis was used to guide the design of the cooling system. This was to ensure that sufficient airflow was introduced and appropriately distributed to cool the telemetry cavity, and hence electronics, without affecting the performance of the engine. Presented herein is a discussion of the telemetry system, instrumentation design philosophy, cooling system design and verification, and sample of the results acquired through successful execution of the full engine test program.

Unbalance Response of a Two Spool Gas Turbine Engine With Squeeze Film Bearings

1981 ◽  
Author(s):  
E. J. Gunter ◽  
D. F. Li ◽  
L. E. Barrett
Keyword(s):  
Gas Turbine ◽  
Nonlinear Effects ◽  
Forced Response ◽  
Squeeze Film ◽  
Gas Generator ◽  
Main Bearing ◽  
Resonant Condition ◽  
Turbine Engine ◽  
Generator Rotor ◽  
Power Turbine

This paper presents a dynamic analysis of a two-spool gas turbine helicopter engine incorporating intershaft rolling element bearings between the gas generator and power turbine rotors. The analysis includes the nonlinear effects of a squeeze film bearing incorporated on the gas generator rotor. The analysis includes critical speeds and forced response of the system and indicates that substantial dynamic loads may be imposed on the intershaft bearings and main bearing supports with an improperly designed squeeze film bearing. A comparison of theoretical and experimental gas generator rotor response is presented illustrating the nonlinear characteristics of the squeeze film bearing. It was found that large intershaft bearing forces may occur even though the engine is not operating at a resonant condition.

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.

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.

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