The ultra-high efficiency gas turbine engine, UHEGT, part I: Design and numerical analysis of the multistage system

2020 ◽  
pp. 095765092095166
Author(s):  
Seyed M Ghoreyshi ◽  
Meinhard T Schobeiri
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Gas Turbines ◽  
High Efficiency ◽  
Combustion Process ◽  
Gas Turbine Engine ◽  
High Pressure Turbine ◽  
Turbine Engine ◽  
Gaseous Fuels ◽  
Multi Stage

The Ultra-High Efficiency Gas Turbine Engine (UHEGT) was introduced in our previous studies. In UHEGT, the combustion process is no longer contained in isolation between the compressor and turbine. It is rather distributed in multiple stages and integrated within the high-pressure turbine stator rows. Compared to the current most advanced conventional gas turbines, UHEGT considerably improves the efficiency and output power of the engine while reducing its emissions and size. In this study, a six-stage UHEGT turbine with three stages of stator internal combustion is designed and analyzed. The design represents a single spool turboshaft system for power generation using gaseous fuels. The preliminary flow path for each turbine stage is designed by the meanline approach and modified using Computational Fluid Dynamics (CFD). Unsteady CFD calculation (via commercial software ANSYS CFX) is used to simulate and optimize the flow and combustion process through high-pressure turbine stages. The results show a base thermal efficiency of above 45% is achieved. It shows a successful integration of the multi-stage combustion process into the high-pressure turbine stages and a highly uniform temperature distribution at the inlet of each rotor row. High temperatures in some areas on the stator blade surfaces are controlled using indexing of fuel injectors and stator blades.

Numerical Simulation of the Multistage Ultra-High Efficiency Gas Turbine Engine, UHEGT

2017 ◽  
Author(s):  
Seyed M. Ghoreyshi ◽  
Meinhard T. Schobeiri
Keyword(s):  
High Pressure ◽  
Temperature Distribution ◽  
Gas Turbine ◽  
Output Power ◽  
High Efficiency ◽  
Combustion Process ◽  
Flow Patterns ◽  
Flow Path ◽  
High Pressure Turbine ◽  
Turbine Engine

The Ultra-High Efficiency Gas Turbine Engine (UHEGT) was introduced in our previous studies [1]–[3]. In UHEGT, the combustion process is no longer contained in isolation between the compressor and turbine, rather distributed in multiple stages and integrated within the high-pressure turbine stator rows. Compared to the current most advanced conventional gas turbines, UHEGT considerably improves the efficiency and output power of the engine while reducing its emissions and size. In the present study, a complete six-stage turbine with three stator internal combustors is designed for UHEGT. The turbine is designed for a single spool turboshaft system used for power generation. A thermodynamic cycle that has a base thermal efficiency of above 45% is designed based on an ideal mixture of methane and air. Preliminary flow path for each turbine stage is designed by 1D/2D approach (meanline calculation). The combustors, designed based on our previous [1] and parallel studies, consist of cylindrical tubes extended from hub to shroud with thin slots on top and bottom for gaseous fuel injection. CFD calculation (via ANSYS CFX) is used to simulate the high pressure turbine stages (stage 1 to 3). The simulations are unsteady, they are performed for ten total components and include a multi-species combustion process along with the rotor motion. The flow path is modified based on the CFD results in order to reduce separation and losses while enabling maximum mixing of fuel and air and reducing temperature non-uniformities. Flow patterns, secondary flow losses, temperature distribution, and pollutant emissions are presented and analyzed in the results. The results show that a relatively uniform temperature distribution is achieved at the inlet of each rotor and the system performs very well regarding the output power and flow patterns.

Investigation of the Transient Response of a Dual-Rotor System With Intershaft Squeeze Film Damper

1985 ◽  
Author(s):  
Qihan Li ◽  
James F. Hamilton
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Transient Response ◽  
Synthesis Method ◽  
Gas Turbine Engine ◽  
Rotor System ◽  
Squeeze Film ◽  
High Pressure Turbine ◽  
Turbine Engine ◽  
Squeeze Film Damper

A method is presented for calculating the dynamics of a dual-rotor gas turbine engine equipped with a flexible intershaft squeeze-film damper. The method is based on the functional expansion component synthesis method. The transient response of the rotor due to a suddenly applied unbalance in the high-pressure turbine under different steady-speed operations is calculated. The damping effects of the intershaft damper and stability of the rotor system are investigated.

Development of the design scheme of cooling for a nozzle vane of high pressure turbine of gas turbine engine

2016 ◽  
Vol 59 (1) ◽  
pp. 58-63 ◽  
Author(s):  
A. V. Vikulin ◽  
N. L. Yaroslavtsev ◽  
V. A. Chesnova
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
High Pressure Turbine ◽  
Turbine Engine ◽  
Nozzle Vane ◽  
Design Scheme

Two Stage Slagging Combustor Design for a Coal-Fueled Industrial Gas Turbine

1991 ◽  
Author(s):  
L. H. Cowell ◽  
R. T. LeCren ◽  
C. E. Tenbrook
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Combustion Zone ◽  
Combustion Process ◽  
Coal Ash ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Full Size ◽  
Primary Zone ◽  
Industrial Gas Turbine

A full size combustor for a coal-fueled industrial gas turbine engine has been designed and fabricated. The design is based on extensive work completed through one-tenth scale combustion tests. Testing of the combustion hardware will be completed with a high pressure air supply in a combustion test facility before the components are integrated with the gas turbine engine. The combustor is a two-staged, rich-lean design. Fuel and air are introduced in the primary combustion zone where the combustion process is initiated. The primary zone operates in a slagging mode inertially removing coal ash from the gas stream. Four injectors designed for coal-water mixture (CWM) atomization are used to introduce the fuel and primary air. In the secondary combustion zone additional air is injected to complete the combustion process at fuel lean conditions. The secondary zone also serves to reduce the gas temperatures exiting the combustor. Between the primary and secondary zones is a Particulate Rejection Impact Separator (PRIS). In this device much of the coal ash that passes from the primary zone is inertially separated from the gas stream. The two-staged combustor along with the PRIS have been designated as the combustor island. All of the combustor island components are refractory lined to minimize heat loss. Fabrication of the combustor has been completed. The PRIS is still under construction. The combustor hardware is being installed at the Caterpillar Technical Center for high pressure test evaluation. The design, test installation, and test plan of the full size combustor island are discussed.

Dynamic Behavior of the Ultra-High Efficiency Gas Turbine Engine, UHEGT, With Stator Internal Combustion

2019 ◽  
Author(s):  
Seyed M. Ghoreyshi ◽  
Meinhard T. Schobeiri
Keyword(s):  
Gas Turbine ◽  
Dynamic Behavior ◽  
Dynamic Simulation ◽  
High Efficiency ◽  
Time Lag ◽  
Combustion Process ◽  
Internal Combustion ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Fuel Flow

Abstract The paper investigates the dynamic behavior of an Ultra-High Efficiency Gas Turbine Engine (UHEGT) with Stator Internal Combustion. The UHEGT-technology was introduced for the first time to the gas turbine design community at the Turbo Expo 2015. In developing the UHEGT-technology, the combustion process is no longer contained in isolation between the compressor and turbine, rather distributed in the first three HP-turbine stator rows. Noticeable improvement in the engine thermal efficiency and power along with other performance advantages are brought by this technology. In the current paper, a dynamic simulation is performed on the entire gas turbine engine (UHEGT) using the nonlinear dynamic simulation code GETRAN. The simulations are in 2D (space-time) and include the majority of the engine components including rotor shaft, turbine and compressor, fuel injectors, diffuser, pipes, valves, controllers, etc. The thermo-fluid conservation laws are applied to the flow in each component which create a system of nonlinear partial differential equations that is solved numerically. Two different fuel schedules (steep rise and Gaussian) are applied to all injectors and the engine response is studied in each case. The results show that fluctuations in the fuel flow lead to fluctuations in most of the system parameters such as temperatures, power, shaft speed, etc. However, the shapes and amplitudes of the fluctuations are different and there is a time lag in the response profiles relative to the fuel schedules. It is shown that an increase in average fuel flow in the system leads to a small drop in efficiency due to the cycle change from the design point. Moreover, it is seen that the temperatures usually rise fast with increase of fuel flow, but the system tends to cool down with a slower rate as the fuel is reduced.

Two-Stage Slagging Combustor Design for a Coal-Fueled Industrial Gas Turbine

1992 ◽  
Vol 114 (2) ◽  
pp. 359-366 ◽  
Author(s):  
L. H. Cowell ◽  
R. T. LeCren ◽  
C. E. Tenbrook
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Combustion Zone ◽  
Combustion Process ◽  
Coal Ash ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Full Size ◽  
Primary Zone ◽  
Industrial Gas Turbine

A full-size combustor for a coal-fueled industrial gas turbine engine has been designed and fabricated. The design is based on extensive work completed through one-tenth scale combustion tests. Testing of the combustion hardware will be completed with a high pressure air supply in a combustion test facility before the components are integrated with the gas turbine engine. The combustor is a two-staged, rich-lean design. Fuel and air are introduced in the primary combustion zone where the combustion process is initiated. The primary zone operates in a slagging mode inertially removing coal ash from the gas stream. Four injectors designed for coal water mixture (CWM) atomization are used to introduce the fuel and primary air. In the secondary combustion zone, additional air is injected to complete the combustion process at fuel lean conditions. The secondary zone also serves to reduce the gas temperatures exiting the combustor. Between the primary and secondary zones is a Particulate Rejection Impact Separator (PRIS). In this device much of the coal ash that passes from the primary zone is inertially separated from the gas stream. The two-staged combustor along with the PRIS have been designated as the combustor island. All of the combustor island components are refractory-lined to minimize heat loss. Fabrication of the combustor has been completed. The PRIS is still under construction. The combustor hardware is being installed at the Caterpillar Technical Center for high pressure test evaluation. The design, test installation, and test plan of the full-size combustor island are discussed.

Investigation of the Transient Response of a Dual-Rotor System With Intershaft Squeeze-Film Damper

1986 ◽  
Vol 108 (4) ◽  
pp. 613-618 ◽  
Author(s):  
Qihan Li ◽  
J. F. Hamilton
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Transient Response ◽  
Synthesis Method ◽  
Gas Turbine Engine ◽  
Rotor System ◽  
Squeeze Film ◽  
High Pressure Turbine ◽  
Turbine Engine ◽  
Squeeze Film Damper

A method is presented for calculating the dynamics of a dual-rotor gas turbine engine equipped with a flexible intershaft squeeze-film damper. The method is based on the functional expansion component synthesis method. The transient response of the rotor due to a suddenly applied imbalance in the high-pressure turbine under different steady-speed operations is calculated. The damping effects of the intershaft damper and stability of the rotor system are investigated.

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