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.

The Split Compressor Differential Gas Turbine Engine for Vehicle Propulsion

1967 ◽  
Vol 89 (1) ◽  
pp. 49-59 ◽  
Author(s):  
G. N. Doyle ◽  
T. S. Wilkinson
Keyword(s):  
Gas Turbine ◽  
Fuel Consumption ◽  
Gas Turbine Engine ◽  
Engine Fuel ◽  
Variable Geometry ◽  
Turbine Engine ◽  
Part Load ◽  
Vehicle Propulsion ◽  
Power Turbine

The performance of the vehicular split compressor differential gas turbine (SCDGT) engine is compared to that of the variable geometry free power turbine (FPT) engine. Fuel consumption, engine braking, acceleration, and starting are considered, and it is concluded that the SCDGT has several important advantages. The SCDGT engine needs no speed-changing gearbox for forward drive, its part-load fuel consumption is at least as good as that of the FPT engine, and its acceleration and ease of starting are better.

LV100 AIPS Technology—For Future Army Propulsion

1992 ◽  
Author(s):  
Walter Brockett ◽  
Angelo Koschier
Keyword(s):  
Control Systems ◽  
Gas Turbine ◽  
Fuel Consumption ◽  
Cooling System ◽  
Gas Turbine Engine ◽  
Air Filtration ◽  
Turbine Engine ◽  
Overall Design ◽  
Armored Vehicle ◽  
And Control

The overall design of and Advanced Integrated Propulsion System (AIPS), powered by an LV100 gas turbine engine, is presented along with major test accomplishments. AIPS was a demonstrator program that included design, fabrication, and test of an advanced rear drive powerpack for application in a future heavy armored vehicle (54.4 tonnes gross weight). The AIPS design achieved significant improvements in volume, performance, fuel consumption, reliability/durability, weight and signature reduction. Major components of AIPS included the recuperated LV100 turbine engine, a hydrokinetic transmission, final drives, self-cleaning air filtration (SCAF), cooling system, signature reduction systems, electrical and hydraulic components, and control systems with diagnostics/prognostics and maintainability features.

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.

Off-Design Characteristics of Low-Fuel Consumption Gas Turbine Engine for Long-Range UAV

2013 ◽  
Author(s):  
Roberto Andriani ◽  
Umberto Ghezzi ◽  
Antonella Ingenito ◽  
Fausto Gamma ◽  
Antonio Agresta
Keyword(s):  
Gas Turbine ◽  
Fuel Consumption ◽  
Long Range ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Design Characteristics

Performance and Emission Characteristics of a Small Scale Gas Turbine Engine Fueled With Propanol/Jet A Blends

2011 ◽  
Author(s):  
Carlos J. Mendez ◽  
Ramkumar N. Parthasarathy ◽  
Subramanyam R. Gollahalli
Keyword(s):  
Gas Turbine ◽  
Fuel Consumption ◽  
Gas Turbine Engine ◽  
Single Stage ◽  
Specific Fuel Consumption ◽  
Small Scale ◽  
Emission Characteristics ◽  
Turbine Engine ◽  
Performance And Emission ◽  
Emission Index

Alcohols serve as an alternate energy resource to the conventional petroleum-based fuels. The objective of this study was to document the performance and emission characteristics of blends of n-propanol and Jet A fuel in a small-scale gas turbine engine. The experiments were conducted in a 30kW gas turbine engine with a single-stage centrifugal flow compressor, annular combustion chamber and a single-stage axial flow turbine. In addition to neat propanol and Jet A fuel, three blends, with 25%, 50% and 75% of propanol by volume, were used as the fuels. The thrust, thrust-specific fuel consumption, and the concentrations of CO and NOx in the exhaust were measured and compared with those measured with Jet A fuel. The engine was operated at the same throttle settings with all the fuels. The operational range of engine rotational speed was shifted downwards with the addition of propanol due to its lower heating value. The thrust specific fuel consumption increased with the addition of propanol, while the CO emission index increased and NOx emission index decreased.

Undergraduate Gas Turbine Engine Design Using Spreadsheets and Commercial Software

2000 ◽  
Author(s):  
Kenneth W. Van Treuren ◽  
Brenda A. Haven
Keyword(s):  
Gas Turbine ◽  
Fuel Consumption ◽  
Pressure Ratio ◽  
Sensitivity Study ◽  
Commercial Software ◽  
Turbine Engine ◽  
Mission Analysis ◽  
Engine Design ◽  
Student Team ◽  
Engine Cycle

A unique, three-part undergraduate gas turbine engine design project was developed to acquaint students, working in teams of two or three, with the process of engine cycle selection. The design application is a low-flying, Close Air Support (CAS) aircraft using a separate exhaust turbofan engine. Both spreadsheets and commercial software are used. The commercial software is included with the course textbook, “Elements of Gas Turbine Propulsion” by Dr Jack D. Mattingly. Using commercial software, reinforced by classroom lectures, allows the students to focus on the design decisions. The first part of the project is Mission Analysis which introduces the student teams to the design problem. A spreadsheet template is given to each student team that includes aircraft and mission profile specifications. The students must complete the spreadsheet and develop the relationships for lift, drag, thrust required, and fuel burn to calculate a useable fuel remaining at the end to the mission. The spreadsheet allows the students to obtain an average specific fuel consumption that results in 1500 lbm of fuel remaining at the end of the mission. This target value is used in the second part of the design process, on-design Parametric Cycle Analysis (PCA), as a basis for engine cycle selection. Parametric Cycle Analysis is accomplished using the program PARA.EXE. PARA.EXE generates a carpet plot of possible engine design choices by varying the compressor pressure ratio, bypass ratio, and fan pressure ratio. From these carpet plots the students must identify three possible engine cycles that meet the target value for specific fuel consumption found during the mission analysis. Tradeoffs between thrust and fuel consumption are discussed and the students are required to justify their choices for the engine cycle. The last part of the project is the off-design Engine Performance Analysis (EPA) using the program PERF.EXE. The chosen engines must fly the mission and meet the required performance and mission constraint. Based on the overall mission performance, the students narrow the field of three possible engine cycles to one. Each student team then does a sensitivity study to determine if there is an additional benefit for slight changes in the design choices. The result of this sensitivity study is the students’ final engine cycle. With this cycle, an additive drag calculation is made using the program DADD.EXE to account for losses (off-design) and these losses are then factored back into the performance spreadsheet to check the engine’s capabilities for completing the mission. The iterative nature of the design process is emphasized throughout but only one pass through the process is accomplished. Units are given in English Engineering, as that is what is required for the project. Both SI and English Engineering units are taught in the course.

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.

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