Development of Embedded Diagnostics for Internal Flow-Field Measurements in Gas Turbine Engines

2004 ◽  
Author(s):  
Gregg Beitel ◽  
Paul Jalbert ◽  
David Plemmons ◽  
Robert Hiers ◽  
Daniel Catalano
Keyword(s):  
Flow Field ◽  
Gas Turbine ◽  
Internal Flow ◽  
Field Measurements ◽  
Turbine Engines ◽  
Gas Turbine Engines

Gas-Dynamics Design of Reversible Turbine for Marine Gas Turbine Engine

2017 ◽  
Author(s):  
Xiying Niu ◽  
Feng Lin ◽  
Weishun Li ◽  
Chen Liang ◽  
Shunwang Yu ◽  
...  
Keyword(s):  
Flow Field ◽  
Gas Turbine ◽  
Gas Dynamics ◽  
Gas Turbine Engine ◽  
Operating Conditions ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Turbine Engine ◽  
Power Turbine ◽  
Full Speed

Gas turbine engines are widely used as the marine main power system. However, they can’t reverse like diesel engine. If the reversal is realized, other ways must be adopted, for example, controllable pitch propeller (CPP) and reversible gearing. Although CPP has widespread use, the actuator installation inside the hub of the propeller lead to the decrease in efficiency, and it takes one minute to switch “full speed ahead” to “full speed astern”. In addition, some devices need to be added for the reversible gearing, and it takes five minutes to switch from “full speed ahead” “to “full speed astern”. Based on the gas turbine engine itself, a reversible gas turbine engine is proposed, which can rotate positively or reversely. Most important of all, reversible gas turbine engine can realize operating states of “full speed ahead”, “full speed astern“ and “stop propeller”. And, it just takes half of one minute to switch “full speed ahead” to “full speed astern”. Since reversible gas turbine engines have compensating advantages, and especially in recent years computational fluid dynamics (CFD) technology and turbine gas-dynamics design level develop rapidly, reversible gas turbine engines will be a good direction for ship astern. In this paper, the power turbine of a marine gas turbine engine was redesigned by three dimensional shape modification, and the flow field is analyzed using CFD, in order to redesign into a reverse turbine. The last stage vanes and blades of this power turbine were changed to double-layer structure. That is, the outer one is reversible turbine, while the inner is the ahead one. Note that their rotational directions are opposite. In order to realize switching between rotation ahead and rotation astern, switching devices were designed, which locate in the duct between the low pressure turbine and power turbine. Moreover, In order to reduce the blade windage loss caused by the reversible turbine during working ahead, baffle plates were used before and after the reversible rotor blades. This paper mainly studied how to increase the efficiency of the reversible turbine stage, the torque change under different operating conditions, rotational speed and rotational directions, and flow field under typical operating conditions. A perfect profile is expected to provide for reversible power turbine, and it can decrease the blade windage loss, and increase the efficiency of the whole gas turbine engine. Overall, the efficiency of the newly designed reversible turbine is up to 85.7%, and the output power is more than 10 MW, which can meet requirements of no less than 30% power of rated condition. Most importantly, the shaft is not over torque under all ahead and astern conditions. Detailed results about these are presented and discussed in the paper.

Experimental and Computational Results of Distributed Combustion for Application in Current Gas Turbine Engine Combustor Architectures

2011 ◽  
Author(s):  
Nick Overman ◽  
Jason Ryon
Keyword(s):  
Flow Field ◽  
Gas Turbine ◽  
Swirling Flow ◽  
Numerical Test ◽  
Injection System ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Lean Burn ◽  
Lean Combustion ◽  
Improved Performance

Current development and testing has lead to a fuel/air injection system for application in gas turbine engines that produces ultra low emissions and stable, lean combustion. The system is designed to operate with current combustor architectures similar to existing gas turbine engines. This paper presents both experimental and numerical test results demonstrating the benefits of such technology including extremely low emissions of NOx, CO, and un-burned hydrocarbons (UHC). Primary focus is on experimental results demonstrating reaction distribution and emissions. Numerical confirmation of flow field dynamics was used to develop an understanding of the re-circulation rates within the combustor and impact on reaction behavior. Several design configurations were tested to investigate the effects of aerodynamic stagnation point and fuel placement with respect to the aerodynamic shear layer produced by the swirling flow field. Test conditions were varied, including inlet air temperature and injector pressure drop for monitoring effects on the operating envelope of distributed reaction and on lean blow out limit. Results demonstrate the improved performance of a system capable of operating in a flameless or distributed reaction mode over that of a typical lean burn system.

Governing Parameters Influencing CMAS Adhesion and Infiltration Into Environmental/Thermal Barrier Coatings in Gas Turbine Engines

2019 ◽  
Author(s):  
Anindya Ghoshal ◽  
Michael J. Walock ◽  
Muthuvel Murugan ◽  
Clara Mock ◽  
Luis Bravo ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Internal Flow ◽  
Turbine Engines ◽  
Splat Morphology ◽  
Gas Turbine Engines ◽  
Substrate Roughness ◽  
Turbine Engine ◽  
Factors Affecting ◽  
Vannevar Bush ◽  
Vertical Lift

Abstract Sand particulate ingestion into modern gas turbine engines for fixed wing and vertical lift aircraft is a significant challenge for both military and civilian missions. ARL as part of a DoD funded Laboratory University Collaborative Initiative (LUCI) and Vannevar Bush Fellowship at UCSD are investigating the governing parameters that primarily influences the CMAS adhesion kinetics and infiltration on the standard Yttria Stabilized Zirconia (YSZ) as part of metallic single crystal Nickel superalloys TBC and SiC/SiC CMC T/EBCs. Current research shows various parameters including CMAS viscosity, porosity, adhesion strength, contact angle (wettability factor), geological factors affecting sand formation, coating and structural substrate roughness and surface temperature, internal flow Reynolds number, temperature, pressure, Mach number, boundary layer and bleed air, coating process (columnar vs splat morphology), tortuosity factor et al affects the CMAS adhesion and infiltration. This paper is a summary of our current research to identify and study the governing parameters that affects the CMAS formation, adhesion and infiltration and the underlying interfaces between CMAS and T/EBC, bond coat and the structural substrate. This work is aligned with Army Modernization Priority Future Vertical Lift and PEO Aviation Advanced Turbine Engine (ATE) Program.

CFD Analysis and Experimental Validation of the Flow Field in a Rib Roughed Turbine Internal Cooling Channel

2018 ◽  
Vol 0 (0) ◽  
Author(s):  
Yasin Sohret ◽  
T. Hikmet Karakoc
Keyword(s):  
Flow Field ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Inlet Temperature ◽  
Internal Cooling ◽  
Gas Turbine Engines ◽  
Cooling Channel ◽  
Turbine Inlet Temperature ◽  
Computational Fluid Dynamics Analysis

Abstract Advances in thermal science force us to develop more efficient systems. The efficiency of widely-used gas turbine engines, is highly dependent on turbine inlet temperature. However, a high turbine inlet temperature yields material deterioration and long term degradation of turbines. To prevent material deterioration, cooling the hot zones of gas turbine engines, particularly turbine components and blades, is a priority. In this way, long term degradation of the turbine is prevented, while the thermal efficiency of the gas turbine engine is boosted. In the current paper, a flow field within a rib roughed blade internal cooling channel is discussed. Within this scope, a computational fluid dynamics analysis is conducted using a Standard k-ω turbulence model. After this, the same case is experimentally investigated. Experimental results obtained from particle image velocimetry measurements are used to validate the results of the computational fluid dynamics analysis. At the end of the study, the flow field is fully mapped with the recirculation and separation zones being clearly pinpointed.

A Pragmatic Approach to Evaluation of Inlet Fogging System Effectiveness

2003 ◽  
Author(s):  
Daniel E. Willems ◽  
Paul D. Ritland
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Free Water ◽  
Field Measurements ◽  
Operating Conditions ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Actual Application ◽  
Temperature Detection ◽  
Laboratory Test Results

The inlet fogging of gas turbine engines has been extensively applied over the past several years. Fogging systems have been predicted to increase gas turbine power output by 10 to 15% based on theoretical and laboratory test results. This paper describes methodology to validate the evaporative cooling effect and quantify performance of inlet fogging systems. A quantitative analysis of inlet fogging systems is provided based on gas turbines operating in different environmental conditions. The tests were conducted on SWPC W501FD Frame gas turbines nominally rated at 185 MW. The data presented herein considers the actual combustion turbine operating conditions, psychrometric considerations and field measurements. This paper also considers the application of specialized temperature measurement equipment suitable for accurate drybulb temperature detection in an environment that may contain free water in the airstream. Theoretical and actual application results are presented to validate the instrument accuracy.

scholarly journals Flow and Thermal Field Measurements in a Combustor Simulator Relevant to a Gas Turbine Aeroengine

2005 ◽  
Vol 127 (2) ◽  
pp. 257-267 ◽  
Author(s):  
S. S. Vakil ◽  
K. A. Thole
Keyword(s):  
Gas Turbine ◽  
High Performance ◽  
Large Scale ◽  
Thermal Field ◽  
Field Measurements ◽  
Turbine Engines ◽  
Laser Doppler Velocimeter ◽  
Gas Turbine Engines ◽  
High Momentum ◽  
Thermal Fields

The current demands for high performance gas turbine engines can be reached by raising combustion temperatures to increase power output. Predicting the performance of a combustor is quite challenging, particularly the turbulence levels that are generated as a result of injection from high momentum dilution jets. Prior to predicting reactions in a combustor, it is imperative that these turbulence levels can be accurately predicted. The measurements presented in this paper are of flow and thermal fields produced in a large-scale combustor simulator, which is representative of an aeroengine. Three-component laser Doppler velocimeter measurements were made to quantify the velocity field while a rake of thermocouples was used to quantify the thermal field. The results indicate large penetration depths for the high momentum dilution jets, which result in a highly turbulent flow field. As these dilution jets interact with the mainstream flow, kidney-shaped thermal fields result due to counter-rotating vortices that develop.

Gas Screen in Components of Gas Turbine Engines

1997 ◽  
Vol 28 (7-8) ◽  
pp. 536-542
Author(s):  
A. A. Khalatov ◽  
I. S. Varganov
Keyword(s):  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Gas Screen

Potential Application of Composite Materials to Future Gas Turbine Engines

1988 ◽  
Author(s):  
James C. Birdsall ◽  
William J. Davies ◽  
Richard Dixon ◽  
Matthew J. Ivary ◽  
Gary A. Wigell
Keyword(s):  
Composite Materials ◽  
Gas Turbine ◽  
Potential Application ◽  
Turbine Engines ◽  
Gas Turbine Engines
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