Aerothermal Research for Turbine Components: An Overview of the European AITEB-2 Project

2010 ◽  
Author(s):  
Erik Janke ◽  
Torsten Wolf
Keyword(s):  
Gas Turbine ◽  
Point Of View ◽  
Cooling Flows ◽  
Technical Work ◽  
Turbine Efficiency ◽  
Thermal Investigations ◽  
Aero Engine ◽  
Future Challenges ◽  
Work Programme ◽  
Frame Work

The 6th European Frame Work Programme project AITEB-2 (Aero-thermal Investigations of Turbine Endwalls and Blades), started in March 2005 and was completed in August 2009. The project consortium of 17 partners brought together major European aero engine and gas turbine manufactures as well as leading European experts in the field of aero-thermodynamics to jointly address future challenges associated with the design of turbine components which are feasible from an aerodynamic, aero-thermal, economic and environmental point of view. The results presented show that the project was conducted successfully. Whereas not all of the ambitious project targets could be achieved, the outcome of both experimental and numerical efforts in the technical work packages lead to significant contributions to a) increased turbine efficiency, b) savings in cooling flows, c) aero-thermal technology for shorter turbine inter-ducts and, d) substantial savings in turn-around times within automated CFD based optimisation approaches.

AERODYNAMICS AND HEAT TRANSFER INSIDE A GAS TURBINE MID-PASSAGE GAP

2021 ◽  
pp. 1-13
Author(s):  
Faisal Shaikh ◽  
Budimir Rosic
Keyword(s):  
Heat Transfer ◽  
Gas Turbine ◽  
Film Cooling ◽  
Heat Load ◽  
Turbine Blades ◽  
Turbine Stage ◽  
Gas Turbine Blades ◽  
Cooling Flows ◽  
Turbine Efficiency ◽  
Gap Flow

Abstract Gas turbine blades and vanes are typically manufactured with small clearances between adjacent vane and blade platforms, termed the midpassage gap. The midpassage gap reduces turbine efficiency and causes additional heat load into the vane platform, as well as changing the distribution of endwall heat transfer and film cooling. This paper presents a low-order analytical analysis to quantify the effects of the midpassage gap on aerodynamics and heat transfer, verified against an experimental campaign and CFD. Using this model, the effects of the gap can be quantified, for a generic turbine stage, based only on geometric features and the passage static pressure field. It is found that at present there are significant losses and a large proportion of heat load caused by the gap, but that with modified design this could be reduced to negligible levels. Cooling flows into the gap to prevent ingression are investigated analytically and with CFD. Recommendations are given for targets that turbine designers should work toward in reducing the adverse effects of the midpassage gap. A method to estimate the effect of gap flow is presented, so that for any machine the significance of the gap may be assessed.

Predicting Compressor of Gas Turbine Power Plant On-Line Washing Interval Using Proportional Hazards Model

2012 ◽  
Vol 452-453 ◽  
pp. 195-199 ◽  
Author(s):  
Lei Zhu ◽  
Hong Fu Zuo
Keyword(s):  
Gas Turbine ◽  
Proportional Hazards ◽  
Proportional Hazards Model ◽  
Prediction Method ◽  
Turbine Efficiency ◽  
Hazards Model ◽  
Aero Engine ◽  
On Line ◽  
Gas Turbine Power Plant ◽  
Over Time

Due to compressor fouling, gas turbine efficiency decreases over time, resulting in decreased power output of the plant. To counteract the effects of compressor fouling, compressor on-line and off-line washing procedures are used. The present research is aimed to propose a method of mathematical modeling of offline washing interval which will be estimated as the RUL of compressor based on Proportional hazards model. Application of the proposed prediction method to the case of Civil Aero-engine proved its effectiveness.

Potential of reducing the environmental impact of aviation by using hydrogen Part II: Aero gas turbine design

2006 ◽  
Vol 110 (1110) ◽  
pp. 541-552
Keyword(s):  
Environmental Impact ◽  
Gas Turbine ◽  
Pressure Ratio ◽  
Point Of View ◽  
Outlet Temperature ◽  
Hydrogen Fuel ◽  
Technical Point ◽  
Engine Design ◽  
Aero Engine ◽  
Turbine Design

Abstract The main objective of the paper is to evaluate the potential of reducing the environmental impact of civil subsonic aviation by using hydrogen fuel. The paper is divided into three parts of which this is Part II. In Part I the background, prospects and challenges of introducing an alternative fuel in aviation were outlined. In this paper, Part II, the aero engine design when using hydrogen is covered. The subjects of optimum cruising altitude and airport implications of introducing liquid hydrogen-fuelled aircraft are raised in Part III. The study shows that burning hydrogen in an aero gas turbine seems to be feasible from a technical point of view. If the priority is to lower the mission fuel consumption, the results indicate that an engine employing increased combustor outlet temperature, overall pressure ratio and by-pass ratio, seems to be the most attractive choice. The mission NOx emissions, on the other hand, seem to be reduced by using engines with a weak core and lowered by-pass ratio.

Automated Repair and Overhaul of Aero-Engine and Industrial Gas Turbine Components

2005 ◽  
Author(s):  
Claus Bremer
Keyword(s):  
Data Management ◽  
Gas Turbine ◽  
Repair Process ◽  
Point Of View ◽  
Data Management System ◽  
Data Set ◽  
Adaptive Machining ◽  
Aero Engine ◽  
Engine Components ◽  
Industrial Gas Turbine

Automated repair processes and adaptive machining strategies constitute an important task in today’s aero-engine and industrial gas turbine maintenance, repair and overhaul (MRO) industry (figure 1). Currently, the repair of blisks is a central issue whenever consideration is given to replacing bladed stages with blisks; the feasibility of such a step hinges on the available capabilities for automated repair. The standard repairs are also influenced by these innovative approaches. Today, most of the processes for the MRO of engine components are carried out manually. In many cases, however, manual operations are not satisfactory from the point of view of costs and reliability. The MRO steps which are especially time consuming and require a high degree of accuracy are inspection, welding, milling and polishing. Adaptive machining methods can compensate for part-to-part variation as well as inaccurate clamping positions and keep the tolerances for the actual parts within a minimal range. The geometrical adaptation of the NC paths to the actual part geometry is performed automatically using in-process measuring techniques, mathematical best-fit strategies and adaptation methods. With the present state-of-the-art, it is possible to automate MRO work steps currently performed manually and to reduce costs and throughput times while boosting quality and precision. A further important aspect for the automation of component repair is the data management which should constitute the core of automated overhaul systems. As part of an innovative data management solution, the single repair process modules are integrated to build an automated repair cell for aero engine components. Furthermore, it is possible to establish “virtual” MRO workshops. The data management system generates a data set for each individual component and handles the logistics of the components and the accompanying data sets. As result, different MRO processes can be carried out at different facilities without loss of information, efficiency or quality. In addition, the approach described supports efficient life cycle monitoring.

Development and Assessment of Combustion Models for Gas Turbine and Aero-Engine Applications

2015 ◽  
Author(s):  
Jan E. Anker ◽  
Dirk Wunsch ◽  
Luigi Romagnosi ◽  
Kilian Claramunt ◽  
Charles Hirsch
Keyword(s):  
Gas Turbine ◽  
Combustion Process ◽  
Measurement Data ◽  
Point Of View ◽  
Navier Stokes ◽  
Flammability Limits ◽  
Combustion Models ◽  
Spray Flames ◽  
Aero Engine ◽  
Combustion Processes

The classical flamelet method, the new Flamelet Generated Manifolds method (FGM), and the hybrid BML/flamelet approach are assessed in the context of the Reynolds-averaged Navier-Stokes (RANS) equations on a large range of configurations for both gaseous and spray flames. The conceptual differences, advantages, and shortcomings of the models are discussed in detail both from a theoretical and a practical point of view. In order to assess the models under gas turbine like conditions, the reactive flow in TU Darmstadt’s Generic Gas Turbine (GGT), DLR Stuttgart’s PRECCINSTA burner, and a premixed industrial combustor are computed. The computational results are compared to available measurement data and are used to discuss the strengths and the weaknesses of each of the aforementioned combustion models. In the current study it is shown that the hybrid BML/flamelet method globally performs well, but that it can be difficult to obtain a burning solution with this method, especially when the combustion process is operated close to the flammability limits. While the flamelet method is very robust, it is outperformed by the FGM method even for purely non-premixed configurations. It is demonstrated that the FGM approach can be used for the whole range of combustion modes, from non-premixed over to premixed combustion processes. Since the model did not lead to any difficulties with attaining a burning solution, and is computationally as efficient as the flamelet approach, the authors recommend the usage of this model over the other models investigated.

Aerodynamics and Heat Transfer Inside a Gas Turbine Mid-Passage Gap

2020 ◽  
Author(s):  
Faisal Shaikh ◽  
Budimir Rosic
Keyword(s):  
Heat Transfer ◽  
Gas Turbine ◽  
Film Cooling ◽  
Heat Load ◽  
Turbine Blades ◽  
Turbine Stage ◽  
Gas Turbine Blades ◽  
Cooling Flows ◽  
Turbine Efficiency ◽  
Gap Flow

Abstract Gas turbine blades and vanes are typically manufactured with small clearances between adjacent vane and blade platforms, termed the midpassage gap. The midpassage gap reduces turbine efficiency and causes additional heat load into the vane platform, as well as changing the distribution of endwall heat transfer and film cooling. This paper presents a low-order analytical analysis to quantify the effects of the midpassage gap on aerodynamics and heat transfer, verified against an experimental campaign and CFD. Using this model, the effects of the gap can be quantified, for a generic turbine stage, based only on geometric features and the passage static pressure field. It is found that at present there are significant losses and a large proportion of heat load caused by the gap, but that with modified design this could be reduced to negligible levels. Cooling flows into the gap to prevent ingression are investigated analytically and with CFD. Recommendations are given for targets that turbine designers should work toward in reducing the adverse effects of the midpassage gap. A method to estimate the effect of gap flow is presented, so that for any machine the significance of the gap may be assessed.

scholarly journals Comprehensive Thermodynamic Analysis of the Humphrey Cycle for Gas Turbines with Pressure Gain Combustion

Energies ◽  
2018 ◽  
Vol 11 (12) ◽  
pp. 3521 ◽  
Author(s):  
Panagiotis Stathopoulos
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Combustion Process ◽  
Ideal Gas ◽  
Point Of View ◽  
Pressure Gain Combustion ◽  
Combustion Technology ◽  
Secondary Air ◽  
And Performance ◽  
The Impact

Conventional gas turbines are approaching their efficiency limits and performance gains are becoming increasingly difficult to achieve. Pressure Gain Combustion (PGC) has emerged as a very promising technology in this respect, due to the higher thermal efficiency of the respective ideal gas turbine thermodynamic cycles. Up to date, only very simplified models of open cycle gas turbines with pressure gain combustion have been considered. However, the integration of a fundamentally different combustion technology will be inherently connected with additional losses. Entropy generation in the combustion process, combustor inlet pressure loss (a central issue for pressure gain combustors), and the impact of PGC on the secondary air system (especially blade cooling) are all very important parameters that have been neglected. The current work uses the Humphrey cycle in an attempt to address all these issues in order to provide gas turbine component designers with benchmark efficiency values for individual components of gas turbines with PGC. The analysis concludes with some recommendations for the best strategy to integrate turbine expanders with PGC combustors. This is done from a purely thermodynamic point of view, again with the goal to deliver design benchmark values for a more realistic interpretation of the cycle.

scholarly journals Current Status of Ceramic Gas Turbine (CGT302)

1998 ◽  
Author(s):  
Hirotake Kobayashi ◽  
Tetsuo Tatsumi ◽  
Takashi Nakashima ◽  
Isashi Takehara ◽  
Yoshihiro Ichikawa
Keyword(s):  
Gas Turbine ◽  
Thermal Efficiency ◽  
Technology Development ◽  
Development Program ◽  
Point Of View ◽  
Current Status ◽  
Fiscal Year ◽  
Inlet Temperature ◽  
Development Organization ◽  
New Energy

In Japan, from the point of view of energy saving and environmental protection, a 300kW Ceramic Gas Turbine (CGT) Research and Development program started in 1988 and is still continuing as a part of “the New Sunshine Project” promoted by the Ministry of International Trade and Industry (MITT). The final target of the program is to achieve 42% thermal efficiency at 1350°C of turbine inlet temperature (TIT) and to keep NOx emissions below present national regulations. Under contract to the New Energy and Industrial Technology Development Organization (NEDO), Kawasaki Heavy Industries, Ltd. (KHI) has been developing the CGT302 with Kyocera Corporation and Sumitomo Precision Products Co., Ltd. By the end of the fiscal year 1996, the CGT302 achieved 37.0% thermal efficiency at 1280°C of TIT. In 1997, TIT reached 1350°C and a durability operation for 20 hours at 1350°C was conducted successfully. Also fairly low NOx was proved at 1300°C of TIT. In January 1998, the CGT302 has achieved 37.4% thermal efficiency at 1250°C TIT. In this paper, we will describe our approaches to the target performance of the CGT302 and current status.

Some Possible Lines of Development in Aircraft Engines

1921 ◽  
Vol 25 (123) ◽  
pp. 130-165
Keyword(s):  
Present State ◽  
State Of The Art ◽  
Point Of View ◽  
Aircraft Engines ◽  
Aero Engine ◽  
The Ideal

In the following paper the writer's aim is to indicate certain possible lines of development and research which his own investigations and preliminary experiments have shown to be at least worthy of serious consideration.If we review the present state of the art we find the position to be substantially as follows :—From a thermodynamic point of view the performance of the modern aero engine has approached so nearly to the ideal obtainable from the cycle on which it operates that there is little scope for improvement.

Towards Improved Prediction of Aero-Engine Combustor Performance Using Large Eddy Simulations

2008 ◽  
Author(s):  
S. James ◽  
M. S. Anand ◽  
B. Sekar
Keyword(s):  
Gas Turbine ◽  
Radial Profile ◽  
Design Tool ◽  
Operating Conditions ◽  
Outlet Temperature ◽  
Gas Turbine Combustor ◽  
Systematic Assessment ◽  
Eddy Simulation ◽  
Large Eddy ◽  
Aero Engine

The paper presents an assessment of large eddy simulation (LES) and conventional Reynolds averaged methods (RANS) for predicting aero-engine gas turbine combustor performance. The performance characteristic that is examined in detail is the radial burner outlet temperature (BOT) or fuel-air ratio profile. Several different combustor configurations, with variations in airflows, geometries, hole patterns and operating conditions are analyzed with both LES and RANS methods. It is seen that LES consistently produces a better match to radial profile as compared to RANS. To assess the predictive capability of LES as a design tool, pretest predictions of radial profile for a combustor configuration are also presented. Overall, the work presented indicates that LES is a more accurate tool and can be used with confidence to guide combustor design. This work is the first systematic assessment of LES versus RANS on industry-relevant aero-engine gas turbine combustors.

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