Fundamental Analysis of a First Stage Ramjet-Rocket Combined Cycle and Second Stage Hydrolysis Propulsion System with Trajectory Weighting

2011 ◽  
Author(s):  
Robert Lemoyne
Keyword(s):  
Combined Cycle ◽  
Propulsion System ◽  
Fundamental Analysis ◽  
Second Stage

Test Verification of Water Cooled Gas Turbine Technology

1981 ◽  
Author(s):  
M. W. Horner ◽  
G. A. Cincotta ◽  
A. Caruvana
Keyword(s):  
Turbine Rotor ◽  
Combined Cycle ◽  
Operating Conditions ◽  
Scale Model ◽  
Technology Readiness ◽  
Integrated Gasification Combined Cycle ◽  
Second Stage ◽  
Verification Test ◽  
Integrated Gasification ◽  
Test Verification

This paper presents the results of three significant tests recently performed by GE under the DOE High Temperature Turbine Technology Phase II Program contract. The first test involved a simulated Integrated Gasification Combined Cycle (IGCC) test of a water-cooled composite nozzle exposed to low Btu coal gas at design operating conditions (2600 F + firing temperature, 12 atm pressure). The second test is that of a water-cooled monolithic nozzle, a full-scale model of the second-stage nozzle planned for the Technology Readiness Vehicle Verification Test. The third test demonstrates coolant water delivery, transfer, and metering distribution, from the stationary feed line to the turbine rotor, enroute to individual bucket airfoil coolant passages. These tests successfully demonstrated the IGCC operation with very good results, and show every indication that operation at firing temperatures up to 3000 F is well within the design capability of the water-cooled turbine.

scholarly journals Performance Analysis of Combined Cycle with Air Breathing Derivative Gas Turbine, Heat Recovery Steam Generator, and Steam Turbine as LNG Tanker Main Engine Propulsion System

2020 ◽  
Vol 8 (9) ◽  
pp. 726
Author(s):  
Wahyu Nirbito ◽  
Muhammad Arif Budiyanto ◽  
Robby Muliadi
Keyword(s):  
Performance Analysis ◽  
Steam Turbine ◽  
Gas Turbine ◽  
Steam Generator ◽  
Heat Recovery ◽  
Combined Cycle ◽  
Propulsion System ◽  
Heat Recovery Steam Generator ◽  
Main Engine ◽  
Ship Speed

This study explains the performance analysis of a propulsion system engine of an LNG tanker using a combined cycle whose components are gas turbine, steam turbine, and heat recovery steam generator. The researches are to determine the total resistance of an LNG tanker with a capacity of 125,000 m3 by using the Maxsurf Resistance 20 software, as well as to design the propulsion system to meet the required power from the resistance by using the Cycle-Tempo 5.0 software. The simulation results indicate a maximum power of the system of about 28,122.23 kW with a fuel consumption of about 1.173 kg/s and a system efficiency of about 48.49% in fully loaded conditions. The ship speed can reach up to 20.67 knots.

Turbo/air augmented rocket - A combined cycle propulsion system

1989 ◽  
Author(s):  
A. GANJI ◽  
M. KHADEM ◽  
S. KHANDANI
Keyword(s):  
Combined Cycle ◽  
Propulsion System

ANALYSIS OF A COMBINED BRAYTON/RANKINE CYCLE WITH TWO REGENERATORS IN PARALLEL

2017 ◽  
Vol 16 (2) ◽  
pp. 10
Author(s):  
J. T. dos Santos ◽  
T. M. Fagundes ◽  
E. D. dos Santos ◽  
L. A. Isoldi ◽  
L. A. O. Rocha
Keyword(s):  
Power Generation ◽  
Numerical Simulations ◽  
Mass Flow Rate ◽  
Flow Rate ◽  
Thermal Efficiency ◽  
Rankine Cycle ◽  
Combined Cycle ◽  
Vapor Quality ◽  
Second Stage ◽  
The One

This work presents a configuration of two regenerators in parallel for a power generation Brayton/Rankine cycle where the output power is 10 MW. The working fluids considered for the Brayton and Rankine cycles are air and water, respectively. The addition of a regenerator with the previous existing cycle of this kind resulted in the addition of a second-stage turbine in the Rankine cycle of reheat. The objective of this modification is to increase the thermal efficiency of the combined cycle. In order to examine the efficiency of the new configuration, it is performed a thermodynamic modelling and numerical simulations for both cases: a regular Brayton/Rankine cycle and the one with the proposed changes. At the end of the simulations, the two cycles are compared, and it is seen that the new configuration reaches a 0.9% higher efficiency. In addition, the vapor quality at the exit of the higher turbine is higher, reducing the required mass flow rate in 14%.

scholarly journals Numerical Study of the Axial Gap and Hot Streak Effects on Thermal and Flow Characteristics in Two-Stage High Pressure Gas Turbine

Energies ◽  
2018 ◽  
Vol 11 (10) ◽  
pp. 2654 ◽  
Author(s):  
Myung Gon Choi ◽  
Jaiyoung Ryu
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Power Plants ◽  
Numerical Study ◽  
Flow Characteristics ◽  
Suction Side ◽  
Combined Cycle ◽  
Maximum Temperature ◽  
Two Stage ◽  
Second Stage

Combined cycle power plants (CCPPs) are becoming more important as the global demand for electrical power increases. The power and efficiency of CCPPs are directly affected by the performance and thermal efficiency of the gas turbines. This study is the first unsteady numerical study that comprehensively considers axial gap (AG) in the first-stage stator and first-stage rotor (R1) and hot streaks in the combustor outlet throughout an entire two-stage turbine, as these factors affect the aerodynamic performance of the turbine. To resolve the three-dimensional unsteady-state compressible flow, an unsteady Reynolds-averaged Navier–Stokes (RANS) equation was used to calculate a k-ω SST γ turbulence model. The AG distance d was set as 80% (case 1) and 120% (case 3) for the design value case 2 (13 mm or d/Cs1 = 0.307) in a GE-E3 gas turbine model. Changes in the AG affect the overall flow field characteristics and efficiency. If AG decreases, the time-averaged maximum temperature and pressure of R1 exhibit differences of approximately 3 K and 400 Pa, respectively. In addition, the low-temperature zone around the hub and tip regions of R1 and second-stage rotor (R2) on the suction side becomes smaller owing to a secondary flow and the area-averaged surface temperature increases. The area-averaged heat flux of the blade surface increases by a maximum of 10.6% at the second-stage stator and 2.8% at R2 as the AG decreases. The total-to-total efficiencies of the overall turbine increase by 0.306% and 0.295% when the AG decreases.

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