Probabilistic Thermal Analysis of Gas Turbine Internal Hardware

2006 ◽  
Author(s):  
Ethan Stearns ◽  
Dave Cloud ◽  
Tom Filburn
Keyword(s):  
Thermal Analysis ◽  
Gas Turbine ◽  
Mass Flow ◽  
Thermal Analyses ◽  
Flow Analysis ◽  
Engine Performance ◽  
Labyrinth Seal ◽  
Metal Temperature ◽  
Initial Development ◽  
Probabilistic Flow

This paper documents the initial development of a method to perform probabilistic thermal analyses of gas turbine internal hardware and uses the turbine interstage seal of a turbofan engine as an example. The purpose of this analysis is to investigate the variability in steady state metal temperature due to variability in the secondary flow system. In addition to quantifying the variability in metal temperature, the sensitivity of the temperature to individual input variables is determined. As a prerequisite for a probabilistic thermal analysis, a probabilistic flow analysis was executed, with variability in engine performance and hardware geometry yielding variability in mass flow rates, heat generation and local swirl velocity. These outputs were used as stochastic inputs for the probabilistic thermal analysis. The analysis was run with correlated input as well as independently varying inputs. The results of this analysis showed that the metal temperature at the tip of the seal was sensitive and highly correlated to air source temperature, as expected. The mass flow rate of air across the seal and heat transfer coefficient also affected the metal temperature. By using correlated input variability, it is shown that variability in metal temperature is ultimately caused by variability in labyrinth seal clearance.

Leakage flow analysis in the gas turbine shroud gap

2019 ◽  
Vol 91 (8) ◽  
pp. 1077-1085 ◽  
Author(s):  
Filip Wasilczuk ◽  
Pawel Flaszynski ◽  
Piotr Kaczynski ◽  
Ryszard Szwaba ◽  
Piotr Doerffer ◽  
...  
Keyword(s):  
Numerical Simulation ◽  
Gas Turbine ◽  
Mass Flow ◽  
Labyrinth Seal ◽  
Leakage Flow ◽  
Original Design ◽  
Reference Case ◽  
Content Type ◽  
Flow Through ◽  
The Impact

Purpose The purpose of the study is to measure the mass flow in the flow through the labyrinth seal of the gas turbine and compare it to the results of numerical simulation. Moreover the capability of two turbulence models to reflect the phenomenon will be assessed. The studied case will later be used as a reference case for the new, original design of flow control method to limit the leakage flow through the labyrinth seal. Design/methodology/approach Experimental measurements were conducted, measuring the mass flow and the pressure in the model of the labyrinth seal. It was compared to the results of numerical simulation performed in ANSYS/Fluent commercial code for the same geometry. Findings The precise machining of parts was identified as crucial for obtaining correct results in the experiment. The model characteristics were documented, allowing for its future use as the reference case for testing the new labyrinth seal geometry. Experimentally validated numerical model of the flow in the labyrinth seal was developed. Research limitations/implications The research studies the basic case, future research on the case with a new labyrinth seal geometry is planned. Research is conducted on simplified case without rotation and the impact of the turbine main channel. Practical implications Importance of machining accuracy up to 0.01 mm was found to be important for measuring leakage in small gaps and decision making on the optimal configuration selection. Originality/value The research is an important step in the development of original modification of the labyrinth seal, resulting in leakage reduction, by serving as a reference case.

scholarly journals Simulation and Flow Analysis of the Hole Diaphragm Labyrinth Seal at Several Whirl Frequencies

Energies ◽  
2022 ◽  
Vol 15 (1) ◽  
pp. 379
Author(s):  
Xiang Zhang ◽  
Yinghou Jiao ◽  
Xiuquan Qu ◽  
Guanghe Huo ◽  
Zhiqian Zhao
Keyword(s):  
Gas Turbine ◽  
Reverse Flow ◽  
Fluid Dynamic ◽  
Dynamic Performance ◽  
Flow Analysis ◽  
Labyrinth Seal ◽  
Unusual Phenomenon ◽  
Complex Fluid ◽  
Turbine Design ◽  
Velocity Turbulence

The seal is designed to reduce leakage and improve the efficiency of gas turbine machines, and is an important technology that needs to be studied in gas turbine design. A series of seals were proposed to try to achieve this goal. However, due to the complex fluid dynamic performance of the seal-rotor system, the seal structure can obtain both the best leakage performance and best rotordynamic performance. This paper presents a detailed flow analysis of the hole diaphragm labyrinth seal (HDLS) at several whirl frequencies and several rotation speeds. The pressure drop, velocity, turbulence kinetic energy and leakage performance of the HDLS were discussed by simulations. An interesting exponential–type relationship between rotation speeds and leakage flow at different whirl frequencies was observed by curve fitting technology. A reverse flow rate was proposed to describe such an unusual phenomenon. Such a relationship can be used to further establish the leakage model of the HDLS and other similar seals.

Accurate Field Compressor Inlet Flow Measurement System

2019 ◽  
Author(s):  
Joshua McConkey ◽  
Richard H. Bunce ◽  
Heiko Claussen
Keyword(s):  
Pressure Drop ◽  
Gas Turbine ◽  
Mass Flow ◽  
Measurement System ◽  
Flow Measurement ◽  
Engine Performance ◽  
Flow Meters ◽  
Air Mass ◽  
Safety Margins ◽  
Compressor Inlet

Abstract Understanding the amount of air that enters a gas turbine is important for calculating their performance and efficiency. Flow meters are almost never used to measure that flow in production engines. Typical flow meters are impractical because the air flow into the compressor is very large, up to 1400 lbs/s (635 kg/s) or 1,000,000 ft3/min (28,300 m3/min), and typically an intentional pressure drop is involved in the measurement. This pressure drop negatively impacts the performance of the engine. If inlet air mass flow were known accurately without negatively impacting the engine performance, then engines could be run more efficiently. Currently, inlet mass flow is typically inferred, rather than measured. This leads to increased safety margins which require engines to be run more conservatively, i.e., at lower power. This paper describes a novel, inexpensive, and accurate air mass flow measurement system with negligible impact on engine performance.

A Study on the Flow and Thermal Stress Analysis of the Hot Gas Casing of the Gas Turbine

2006 ◽  
Vol 306-308 ◽  
pp. 169-174
Author(s):  
Young Jin Choi ◽  
Young Shin Lee ◽  
Jae Hoon Kim ◽  
Won Shik Park ◽  
Hyun Soo Kim
Keyword(s):  
Thermal Analysis ◽  
Thermal Stress ◽  
Stress Analysis ◽  
Gas Turbine ◽  
Flow Analysis ◽  
Load Condition ◽  
Temperature Data ◽  
Thermal Gradients ◽  
Thermal Stress Analysis ◽  
Hot Gas

The hot gas casing of the gas turbine has operated in high temperatures and thermal gradients. The structure safety of hot gas casing will be highly depend on the thermal stress. In this paper, flow and thermal stress analysis of the hot gas casing is carried out using ANSYS program. The obtained temperature data by flow analysis of hot gas casing is applied to the load condition of the thermal analysis. The thermal stress analysis is carried out the elastic-plasticity analysis. The pressure, temperature and velocity of the flow and thermal stress of the hot gas casing are presented

CFD Analyses of Flow in a Gas Turbine Combustor Swirl Cup

2017 ◽  
Author(s):  
Srinivasan Karuppannan ◽  
Bhirud Mehul ◽  
Gullapalli Sivaramakrishna ◽  
Raju D. Navindgi ◽  
N. Muthuveerappan
Keyword(s):  
Gas Turbine ◽  
Mass Flow ◽  
Flow Behavior ◽  
Flow Analysis ◽  
Operating Regime ◽  
Gas Turbine Combustor ◽  
Ansys Fluent ◽  
Turbine Engine ◽  
Downstream Flow ◽  
Cfd Analyses

Swirl cups (hybrid atomizers) are being widely employed in aero gas turbine engine combustors for their established merits in terms of achieving satisfactory atomization over the entire combustor operating regime. Even though several investigators have worked on development of these swirl cups, there is a scanty data reported in literature relevant to their design. In the present study, flow behavior in a swirl cup assembled in a confined chamber similar to a gas turbine combustor has been analyzed. Flow analysis has been carried out using ANSYS Fluent and turbulence has been modeled using Realizable k-ϵ model. Six swirl cup configurations have been analyzed; mass flow ratio between primary and secondary swirler and venturi converging area ratio have been varied. The effect of these parameters on downstream flow field has been studied by analyzing the profiles of axial, tangential and radial velocities downstream of swirl cup. The size and shape of the recirculation zone has been analyzed and reported for all configurations. Also, the mass flow recirculated by swirl cup has been estimated and compared amongst the configurations analyzed. Data thus generated is very useful in designing such swirl cups of gas turbine combustors.

Refitting of Exhaust Diffuser of Industrial Gas Turbine

2008 ◽  
Author(s):  
Vladimir Vassiliev ◽  
Matthias Rothbrust ◽  
Stefan Irmisch
Keyword(s):  
Mach Number ◽  
Gas Turbine ◽  
Mass Flow ◽  
Power Output ◽  
Engine Performance ◽  
Aerodynamic Optimization ◽  
Expansion Turbine ◽  
Higher Power ◽  
Industrial Gas Turbine

This paper describes the aerodynamic optimization of the GT26 exhaust diffuser. The need for optimization was triggered by an upgrade of the compressor, resulting in a higher mass flow and a higher power output. The expansion turbine remained unchanged. However, the increase in mass flow had a significant impact on the Mach number. Secondly, the residual swirl at the turbine outlet, and therefore, the exhaust loss in original diffuser would have increased. The re-optimization of diffuser allowed minimization of the losses and improvement of the overall engine performance.

scholarly journals The CW251B12 Gas Turbine Engine

1989 ◽  
Author(s):  
Ihor S. Diakunchak
Keyword(s):  
Gas Turbine ◽  
Mass Flow ◽  
Firing Temperature ◽  
Engine Performance ◽  
Performance Information ◽  
Turbine Engine ◽  
Integrity Verification ◽  
Full Load ◽  
Modest Increase ◽  
Improved Performance

The latest variant of the W251 family of engines, the CW251B12, rated at 48 MW, is described in this paper. The improved performance, compared to the CW251B10 model, is achieved by the redesign of the compressor for increased mass flow and efficiency and by hot end modifications, which allow a modest increase in firing temperature. Some of the details of the compressor redesign and turbine modifications are outlined. The uprated engine performance information is provided, as well as plans for the full load factory Prototype tests for engine performance and mechanical integrity verification.

Design, Development and Application of Vehicle Gas Turbine Engines

1966 ◽  
Vol 181 (1) ◽  
pp. 149-172
Author(s):  
P. A. Phillips ◽  
Peter Spear
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Low Cost ◽  
Engine Performance ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Design Development ◽  
Turbine Engine ◽  
Wide Range ◽  
Cycle Temperature

After briefly summarizing worldwide automotive gas turbine activity, the paper analyses the power plant requirements of a wide range of vehicle applications in order to formulate the design criteria for acceptable vehicle gas turbines. Ample data are available on the thermodynamic merits of various gas turbine cycles; however, the low cost of its piston engine competitor tends to eliminate all but the simplest cycles from vehicle gas turbine considerations. In order to improve the part load fuel economy, some complexity is inevitable, but this is limited to the addition of a glass ceramic regenerator in the 150 b.h.p. engine which is described in some detail. The alternative further complications necessary to achieve satisfactory vehicle response at various power/weight ratios are examined. Further improvement in engine performance will come by increasing the maximum cycle temperature. This can be achieved at lower cost by the extension of the use of ceramics. The paper is intended to stimulate the design application of the gas turbine engine.

Thermal Analysis of Cooling System in a Gas Turbine Transition Piece

2011 ◽  
Author(s):  
Jun Su Park ◽  
Namgeon Yun ◽  
Hokyu Moon ◽  
Kyung Min Kim ◽  
Sin-Ho Kang ◽  
...  
Keyword(s):  
Heat Transfer ◽  
Gas Turbine ◽  
Thermal Stresses ◽  
Cooling System ◽  
Structural Information ◽  
Thermal Analyses ◽  
Thermal Design ◽  
Transfer Coefficients ◽  
Transition Piece ◽  
Inlet Conditions

This paper presents thermal analyses of the cooling system of a transition piece, which is one of the primary hot components in a gas turbine engine. The thermal analyses include heat transfer distributions induced by heat and fluid flow, temperature, and thermal stresses. The purpose of this study is to provide basic thermal and structural information on transition piece, to facilitate their maintenance and repair. The study is carried out primarily by numerical methods, using the commercial software, Fluent and ANSYS. First, the combustion field in a combustion liner with nine fuel nozzles is analyzed to determine the inlet conditions of a transition piece. Using the results of this analysis, pressure distributions inside a transition piece are calculated. The outside of the transition piece in a dump diffuser system is also analyzed. Information on the pressure differences is then used to obtain data on cooling channel flow (one of the methods for cooling a transition piece). The cooling channels have exit holes that function as film-cooling holes. Thermal and flow analyses are carried out on the inside of a film-cooled transition piece. The results are used to investigate the adjacent temperatures and wall heat transfer coefficients inside the transition piece. Overall temperature and thermal stress distributions of the transition piece are obtained. These results will provide a direction to improve thermal design of transition piece.

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