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.

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.

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.

The Development and Testing of a Gas Turbine Engine Foreign Object Damage (FOD) Detection System

2010 ◽  
Author(s):  
D. N. Cardwell ◽  
K. S. Chana ◽  
M. T. Gilboy
Keyword(s):  
Gas Turbine ◽  
Eddy Current ◽  
Engine Speed ◽  
Detection System ◽  
Acoustic Emissions ◽  
Gas Turbine Engine ◽  
Current Sensor ◽  
Foreign Object ◽  
Turbine Engine ◽  
Foreign Object Damage

This paper details the development of a prototype in-flight foreign object damage (FOD) detection system through various stages, resulting in a system capable of detecting objects as small as one gram (1g) mass. The system comprises an eddy current sensor based tip timing system and acoustic emissions vibration sensors controlled through a digital signal processor (DSP). QinetiQ have developed light weight, contamination-immune eddy current tip timing sensors for use in engine health management. Engine tests confirmed these sensors’ potential for detecting FOD events. FOD detection algorithms were developed and implemented in a prototype DSP that was built and tested on an uninstalled gas turbine engine. The trials showed that the prototype DSP FOD detection system could detect dynamic FOD events at full engine speed. Further work was carried out to enhance the FOD detection system, overcoming limitations in the previous system through the implementation of enhanced algorithms and its extension to accept four eddy current sensor inputs as well as a vibration signal input from an acoustic emissions (AE) sensor. An algorithm that computes engine speed from the tip timing data was also implemented to alleviate the need for a separate 1/rev signal. A number of engine trials were successfully completed in order to validate the system. The speed algorithm has been successfully validated on engine trials and comparisons with a conventional optical based 1/rev showed the DSP-generated 1/rev signals to be almost identical to the conventional system. Typically, the error was in the region of 0.03% speed. The investigations culminated in a test series designed to ascertain the system’s sensitivity to foreign object impacts. These demonstrated that the system was capable of detecting objects down to one gram (1g) mass introduced at low speed into the engine intake.

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.

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 Supply of additional working fluid to the flow part of the NK-8 gas turbine engine

2020 ◽  
Vol 178 ◽  
pp. 01038
Author(s):  
George Marin ◽  
Dmitrii Mendeleev ◽  
Boris Osipov ◽  
Azat Akhmetshin
Keyword(s):  
Gas Turbine ◽  
Maximum Load ◽  
Constant Load ◽  
Gas Turbine Engine ◽  
Working Fluid ◽  
Turbine Engine ◽  
Power Turbine ◽  
Mixing Chamber ◽  
Flow Part ◽  
Turbine Installation

Modern energy development strategies of advanced countries are based on the construction of gas turbine units which is associated with sufficiently high values of thermal efficiency and a relatively short term for putting them into operation. In this paper, the NK-8 engine is considered. It is modernized with a mixing chamber and a power turbine for the purpose of its ground application. A study was conducted of the injection of an additional working fluid into the flow part of a dual-circuit gas turbine engine. Steam is used as an injectable substance. For research a mathematical model was created in the AS «GRET» software package. The studies were carried out under constant load, the maximum load during injection was determined. An additional worker can be supplied with summer power limitations when it is necessary to increase the power of a gas turbine installation. Studies have shown that the maximum power that can be obtained by supplying steam to the flow part is 32.2 MW.

Design of a State Space Controller for an Intercooled, Regenerated (ICR) Gas Turbine Engine

1994 ◽  
Author(s):  
Karl F. Prigge ◽  
Jerry W. Watts ◽  
Terrence E. Dwan
Keyword(s):  
Gas Turbine ◽  
Time Constant ◽  
Gas Turbine Engine ◽  
The Other ◽  
Pole Placement ◽  
Inlet Temperature ◽  
Fast Time ◽  
Turbine Engine ◽  
Power Turbine ◽  
Input Control

A multi-input, multi-output (MIMO) controller for an advanced gas turbine has been developed and tested using a computer simulation. The engine modeled is a two-and-one half spool gas turbine with both an intercooler and a regenerator. In addition, variable stator vanes are present in the free-power turbine. This advanced engine is proposed for future naval propulsion for both mechanical drive ships and electrical drive ships. The designed controller controls free-power turbine speed and turbine inlet temperature using fuel flow and angle of the stator vanes. The controller will also have four modes of operation to deal with over temperature and over speed conditions. An eight state reduced order controller was used with pole placement and LQR to arrive at control gains. Both these methods required considerable insight into the problem. This insight was provided by previous experience with controller design for a less complicated engine, and also by use of a polyhedral search model of the gas turbine engine. The difficulty with a MIMO controller was that both inputs affect both of the control variables. The classical resolution of this problem is to have one input control one variable at a fast time constant and the other input control the other variable at a slow time constant. The “optimal” resolution of this problem is analyzed using the transient curves and basic control theory.

The Choice Gas Turbine Engine Parameters Used to Drive the Oil Pump

2017 ◽  
pp. 29-43
Author(s):  
A. Yu. Brycheva ◽  
V. D. Molyakov
Keyword(s):  
Crude Oil ◽  
Gas Turbine ◽  
Fuel Consumption ◽  
Centrifugal Pump ◽  
Gas Turbine Engine ◽  
Airflow Rate ◽  
Turbine Engine ◽  
Oil Pump ◽  
Power Turbine ◽  
Engine Cycle

The article considers capabilities of the gas turbine engine to be used as a drive of the crude oil pump. It is noted that the gas turbine drive proves to be more advantageous than the electric motor when there is no external power supply or building periods of power transmission lines are significantly long, as well as quantities of oil products pumped are often changed.The main objective of this work is to select the optimum engine cycle parameters for a particular pump model, which oil pumping stations use. As an object of research, a crude oil pump of the НМ 10000 / 1.25-210 brand was chosen. The paper presents technical characteristics of the HM 10000 / 1.25-210 centrifugal pump and experimental values of head, power, and efficiency of the pump for a number of feeds. To obtain the pressure and power characteristics of a centrifugal pump for different rotational speeds of the rotor the similarity formulas are used.As the centrifugal pump drive, the paper considers a two-shaft plant with the free power turbine. This scheme was chosen in accordance with the features of the gas turbine pump unit at the oil pumping station. It is noted that the free power turbine scheme allows us to bring into accordance the characteristics of a gas turbine engine and an oil pump in abnormal modes, since there is no mechanical connection between high and low pressure turbines.The paper presents the calculated parameters of the gas turbine engine cycle with power Ne = 8 MW. The graphs show dependence of the airflow rate GB, the specific fuel consumption Ce and the efficiency ηe on the degree of pressure increase πk in the compressor. In accordance with the graphs, the optimum value of the degree of pressure increase πk = 15 in the compressor  is adopted. With πk = 15, the specific fuel consumption in the gas turbine engine with power Ne = 8 MW is equal to Ce = 0,22 kg/kW*h and the airflow rate is GB = 20,5kg/s. The efficiency of the engine with the selected parameters is ηe = 38,4%.It is noted that in order to ensure the most economical gas turbine engine operation, it is necessary to select the optimal control program, which is determined taking into account the load characteristics, in this case the characteristics of the pump.

Telemetry System Integrated in a Small Gas Turbine Engine

2012 ◽  
Vol 134 (4) ◽  
Author(s):  
Stephen A Long ◽  
Stephen L Edney ◽  
Patrick A Reiger ◽  
Michael W Elliott ◽  
Frank Knabe ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Cooling System ◽  
Turbine Rotor ◽  
Gas Turbine Engine ◽  
Telemetry System ◽  
Test Program ◽  
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 gauges. The acquisition of this data necessitated the use of a telemetry system that could be integrated into the existing engine architecture without affecting performance. As a result of space constraints, housing of the telemetry module was limited to placement in a hot section. 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.

Sign in / Sign up

Export Citation Format

Share Document