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.

Potential of reducing the environmental impact of aviation by using hydrogen Part III: Optimum cruising altitude and airport implications

2006 ◽  
Vol 110 (1110) ◽  
pp. 553-565
Keyword(s):  
Environmental Impact ◽  
Liquid Hydrogen ◽  
Point Of View ◽  
Civil Aviation ◽  
Hydrogen Fuel ◽  
Engine Design ◽  
Aero Engine ◽  
Airport Infrastructure ◽  
Cost Implications ◽  
The Cost

AbstractThe 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 III. In Part I the background, prospects and challenges of introducing an alternative fuel in aviation were outlined. The aero engine design when using hydrogen was covered in Part II. In this paper, Part III, the subjects of optimum cruising altitude and airport implications of introducing liquid hydrogen-fuelled aircraft are raised.For minimum global warming, the results of a preliminary analysis associated with large uncertainties suggest that cryoplanes should cruise at an altitude of about 2-3km below where conventional aircraft cruise today. Ignoring the cost implications, from an airport infrastructure point of view, it seems feasible to change to hydrogen use. With respect to the availability of energy, it would be reasonable to change from kerosene to liquid hydrogen as fuel for all civil aviation refuelling in Sweden.

scholarly journals Feasibility of a Helium Closed-Cycle Gas Turbine for UAV Propulsion

2020 ◽  
Vol 11 (1) ◽  
pp. 28
Author(s):  
Emmanuel O. Osigwe ◽  
Arnold Gad-Briggs ◽  
Theoklis Nikolaidis
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Pressure Ratio ◽  
Low Noise ◽  
Closed Cycle ◽  
Propulsion Systems ◽  
Component Design ◽  
Readiness Level ◽  
Aerial Vehicle ◽  
Turbine Design

When selecting a design for an unmanned aerial vehicle, the choice of the propulsion system is vital in terms of mission requirements, sustainability, usability, noise, controllability, reliability and technology readiness level (TRL). This study analyses the various propulsion systems used in unmanned aerial vehicles (UAVs), paying particular focus on the closed-cycle propulsion systems. The study also investigates the feasibility of using helium closed-cycle gas turbines for UAV propulsion, highlighting the merits and demerits of helium closed-cycle gas turbines. Some of the advantages mentioned include high payload, low noise and high altitude mission ability; while the major drawbacks include a heat sink, nuclear hazard radiation and the shield weight. A preliminary assessment of the cycle showed that a pressure ratio of 4, turbine entry temperature (TET) of 800 °C and mass flow of 50 kg/s could be used to achieve a lightweight helium closed-cycle gas turbine design for UAV mission considering component design constraints.

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.

Preliminary Multidisciplinary Design Optimization System: A Software Solution for Early Gas Turbine Conception

2005 ◽  
Author(s):  
Pascal Prado ◽  
Yulia Panchenko ◽  
Jean-Yves Tre´panier ◽  
Christophe Tribes
Keyword(s):  
Design Optimization ◽  
Gas Turbine ◽  
Design Process ◽  
Multidisciplinary Design Optimization ◽  
Software Tool ◽  
Multidisciplinary Design ◽  
Engine Design ◽  
Wide Range ◽  
Speed Up ◽  
Turbine Design

Preliminary Multidisciplinary Design Optimization (PMDO) project addresses the development and implementation of the Multidisciplinary Design Optimization (MDO) methodology in the Concept/Preliminary stages of the gas turbine design process. These initial phases encompass a wide range of coupled engineering disciplines. The PMDO System is a software tool intended to integrate existing design and analysis tools, decompose coupled multidisciplinary problems and, therefore, allow optimizers to speed-up preliminary engine design process. The current paper is a brief presentation of the specifications for the PMDO System as well as a description of the prototype being developed and evaluated. The current assumed e xible architecture is based on three software components that can be installed on different computers: a Java/XML MultiServer, a Java Graphical User Interface and a commercial optimization software.

A Study on an Evaluation of Indirect Cycle Plant Systems for HTGR

2008 ◽  
Author(s):  
Isao Minatsuki ◽  
Sunao Oyama ◽  
Yorikata Mizokami ◽  
Bernard Ballot
Keyword(s):  
Gas Turbine ◽  
Reactor Core ◽  
System Optimization ◽  
Reactor Power ◽  
Combined Cycle ◽  
Point Of View ◽  
Outlet Temperature ◽  
Optimization Study ◽  
Gas Turbine Cycle ◽  
Plant Efficiency

In the world now, several types of indirect system concept have been investigated for the High Temperature Gas cooled Reactor power plant (HTGR). From a point of optimization of HTGR, it is important to investigate and to compare their power conversion systems from a technical and an economical view point. In the first step of this study, an indirect steam cycle (ID-SC), an indirect gas turbine cycle (ID-GT), an indirect gas turbine combined cycle (ID-CCGT) and a direct gas turbine cycle (D-GT) has been chosen as the systems to be compared. The followings are chosen items for comparison analysis: a) Plant efficiency; b) Amount of commodities (which can estimate capital cost); c) Flexibility of reactor core design; d) Technical issues to be developed; e) Compatibility with hydrogen production system, etc. And for the second step, as the system optimization study among the selected system, sensitiveness to plant efficiency by changing the inlet and the outlet temperature of reactor core has been investigated from an economical and plant efficiency point of view.

Parameter Optimization on Combined Gas Turbine-Fuel Cell Power Plants

2005 ◽  
Vol 2 (4) ◽  
pp. 268-273 ◽  
Author(s):  
Rainer Kurz
Keyword(s):  
Fuel Cell ◽  
Gas Turbine ◽  
Power Plants ◽  
Pressure Ratio ◽  
Design Parameters ◽  
Turbine Efficiency ◽  
Compressor Pressure Ratio ◽  
Turbine Design ◽  
Cycle Efficiency ◽  
Compressor Efficiency

A thermodynamic model for a gas turbine-fuel cell hybrid is created and described in the paper. The effects of gas turbine design parameters such as compressor pressure ratio, compressor efficiency, turbine efficiency, and mass flow are considered. The model allows to simulate the effects of fuel cell design parameters such as operating temperature, pressure, fuel utilization, and current density on the cycle efficiency. This paper discusses, based on a parametric study, optimum design parameters for a hybrid gas turbine. Because it is desirable to use existing gas turbine designs for the hybrids, the requirements for this hybridization are considered. Based on performance data for a typical 1600hp industrial single shaft gas turbine, a model to predict the off-design performance is developed. In the paper, two complementary studies are performed: The first study attempts to determine the range of cycle parameters that will lead to a reasonable cycle efficiency. Next, an existing gas turbine, that fits into the previously established range of parameters, will be studied in more detail. Conclusions from this paper include the feasibility of using existing gas turbine designs for the proposed cycle.

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.

Undergraduate Gas Turbine Engine Design Using Spreadsheets and Commercial Software

2000 ◽  
Author(s):  
Kenneth W. Van Treuren ◽  
Brenda A. Haven
Keyword(s):  
Gas Turbine ◽  
Fuel Consumption ◽  
Pressure Ratio ◽  
Sensitivity Study ◽  
Commercial Software ◽  
Turbine Engine ◽  
Mission Analysis ◽  
Engine Design ◽  
Student Team ◽  
Engine Cycle

A unique, three-part undergraduate gas turbine engine design project was developed to acquaint students, working in teams of two or three, with the process of engine cycle selection. The design application is a low-flying, Close Air Support (CAS) aircraft using a separate exhaust turbofan engine. Both spreadsheets and commercial software are used. The commercial software is included with the course textbook, “Elements of Gas Turbine Propulsion” by Dr Jack D. Mattingly. Using commercial software, reinforced by classroom lectures, allows the students to focus on the design decisions. The first part of the project is Mission Analysis which introduces the student teams to the design problem. A spreadsheet template is given to each student team that includes aircraft and mission profile specifications. The students must complete the spreadsheet and develop the relationships for lift, drag, thrust required, and fuel burn to calculate a useable fuel remaining at the end to the mission. The spreadsheet allows the students to obtain an average specific fuel consumption that results in 1500 lbm of fuel remaining at the end of the mission. This target value is used in the second part of the design process, on-design Parametric Cycle Analysis (PCA), as a basis for engine cycle selection. Parametric Cycle Analysis is accomplished using the program PARA.EXE. PARA.EXE generates a carpet plot of possible engine design choices by varying the compressor pressure ratio, bypass ratio, and fan pressure ratio. From these carpet plots the students must identify three possible engine cycles that meet the target value for specific fuel consumption found during the mission analysis. Tradeoffs between thrust and fuel consumption are discussed and the students are required to justify their choices for the engine cycle. The last part of the project is the off-design Engine Performance Analysis (EPA) using the program PERF.EXE. The chosen engines must fly the mission and meet the required performance and mission constraint. Based on the overall mission performance, the students narrow the field of three possible engine cycles to one. Each student team then does a sensitivity study to determine if there is an additional benefit for slight changes in the design choices. The result of this sensitivity study is the students’ final engine cycle. With this cycle, an additive drag calculation is made using the program DADD.EXE to account for losses (off-design) and these losses are then factored back into the performance spreadsheet to check the engine’s capabilities for completing the mission. The iterative nature of the design process is emphasized throughout but only one pass through the process is accomplished. Units are given in English Engineering, as that is what is required for the project. Both SI and English Engineering units are taught in the course.

scholarly journals Efficiency Analysis of the Turbine using Calorific Value Parameters for a 10 Megawatt Gas Turbine

2021 ◽  
pp. 59-66
Author(s):  
Rex K.C Amadi ◽  
Charles David
Keyword(s):  
Ambient Temperature ◽  
Gas Turbine ◽  
Thermal Efficiency ◽  
Pressure Ratio ◽  
Calorific Value ◽  
Operating Conditions ◽  
Outlet Temperature ◽  
Flow Process ◽  
Compressor Work ◽  
Gas Turbine Power Plant

This research is based on the thermodynamic performance of a gas turbine power plant.  It considered the variation of operating conditions, i.e. the ambient temperature, the compressor outlet temperature, pressure ratio, etc. on the performance of the gas turbine thermal efficiency, turbine work, compressor work, etc. which were derived and analyzed.  The Gross (higher) calorific values at constant pressure () heat of combustion in a flow process from state 1 to state 2 was considered and used to analyze our thermal efficiency.  The results show that the ambient temperature and air to fuel ratio strongly influence the turbine work, compressor work and thermal efficiency.  In addition, the thermal efficiency and power decreases linearly with increase of the ambient temperature.  However, the efficiency analyzed when the calorific parameters were considered was higher than the efficiency when the basic thermodynamic theories (first and second law principles) were used.  The first ranges between 31% to 33, while the second ranges between 28% to 32% under the same ambient temperature conditions

The Evolution of Compressor and Turbine Bladings in Gas Turbine Design

1967 ◽  
Vol 89 (2) ◽  
pp. 199-205 ◽  
Author(s):  
C. Seippel
Keyword(s):  
Steam Turbine ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Pressure Ratio ◽  
Parallel Evolution ◽  
Axial Compressor ◽  
Expansion Turbine ◽  
The Stability ◽  
Turbine Design ◽  
The City

The author, having been associated with the construction of gas turbines from the first 4000-kw unit delivered in 1939 to the city of Neuchaˆtel to the present time, gives some personal views on the evolution of the axial compressor and turbine bladings which are the key elements to the gas turbines. The axial compressor was created to supply air efficiently for the supercharged “Velox” boiler. It made the evolution to the modern gas turbine possible. The main problems encountered were related to the stability of flow. An enormous increase of volume capacity was achieved in the course of time. The increase of pressure ratio made special measures necessary to overcome instability at starting. The expansion turbine started on the basis of steam turbine practice and underwent a parallel evolution to large capacities. Its particular problems are related to the high temperatures of the gases.

Sign in / Sign up

Export Citation Format

Share Document