Prewhirl an Added Degree of Freedom to the Designer of Small Single-Shaft Gas Turbines

1967 ◽  
Vol 89 (1) ◽  
pp. 83-85
Author(s):  
A. R. Shouman
Keyword(s):  
Gas Turbines ◽  
Degree Of Freedom ◽  
Design Specifications ◽  
Compressor Inlet ◽  
Design Requirements

The possibility of the advantageous use of adjustable guidevanes in the compressor inlet for the control of single-shaft gas turbines is discussed. Considering certain design specifications that are impossible to be met by a fixed-geometry, single-shaft machine, it is pointed out how the design specifications can be met utilizing an inlet guidevane system. This is merely used as an example to point out the possible merits of such a system and that it may allow the designer to meet some extraordinary design requirements.

A New Inlet Distortion and Pressure Loss Based Design of an Intake System for Stationary Gas Turbines

2013 ◽  
Author(s):  
Jose Rodriguez ◽  
Stephan Klumpp ◽  
Thomas Biesinger ◽  
James O’Brien ◽  
Tobias Danninger
Keyword(s):  
Gas Turbines ◽  
Inlet System ◽  
Inlet Distortion ◽  
Surge Margin ◽  
Compressor Surge ◽  
Compressor Inlet ◽  
The Face ◽  
Flow Quality ◽  
Inlet Manifold ◽  
Distortion Parameters

This paper presents a new design for a Compressor Inlet Manifold (CIM) for a land-based power generation Gas Turbine (turbine). The CIM is the component of the Inlet System (IS) that is directly connected to the turbine via the Compressor Inlet Case (CIC). The design philosophy is to use low fidelity but fast and automated CFD (Computational Fluid Dynamics) for design iterations and then confirm the design with detailed higher accuracy CFD before proceeding to engine tests. New design features include contouring the wall to minimize areas of flow separation and associated unsteadiness and losses, and improvement of the flow quality into the compressor. The CIM in a land-based turbine acts as a nozzle whereas the inlet of an aircraft acts as a diffuser. The flow also enters the CIM at 90 deg to the engine axis. This leads to a pair of counter rotating vortices at the compressor inlet. Three main sources of flow distortions at the face of the compressor are identified: flow separations at outer walls of the IS and CIM struts and the counter rotating vortices. The higher accuracy CFD analysis including the complete IS, CIM and the first compressor stage, simulates the effect of these distortions on the compressor front stage at design conditions. A range of inlet distortion parameters are used to evaluate the inlet design. The well known DC60 based criterion derived from aircraft engines and other less known but published parameters are able to give an indication of how the compressor surge margin of stationary gas turbines is affected.

Design and Testing of a Can Combustor for a Small Gas Turbine Application

2013 ◽  
Author(s):  
K. V. L. Narayana Rao ◽  
N. Ravi Kumar ◽  
G. Ramesha ◽  
M. Devathathan
Keyword(s):  
Mass Flow Rate ◽  
Mass Flow ◽  
Flow Rate ◽  
Gas Turbines ◽  
Pressure Loss ◽  
High Energy ◽  
Experimental Results ◽  
High Mass ◽  
Test Facility ◽  
Design Requirements

Can type combustors are robust, with ease of design, manufacturing and testing. They are extensively used in industrial gas turbines and aero engines. This paper is mainly based on the work carried out in designing and testing a can type combustion chamber which is operated using JET-A1 fuel. Based on the design requirements, the combustor is designed, fabricated and tested. The experimental results are analysed and compared with the design requirements. The basic dimensions of the combustor, like casing diameter, liner diameter, liner length and liner hole distribution are estimated through a proprietary developed code. An axial flow air swirler with 8 vanes and vane angle of 45 degree is designed to create a re-circulation zone for stabilizing the flame. The Monarch 4.0 GPH fuel nozzle with a cone angle of 80 degree is used. The igniter used is a high energy igniter with ignition energy of 2J and 60 sparks per minute. The combustor is modelled, meshed and analysed using the commercially available ansys-cfx code. The geometry of the combustor is modified iteratively based on the CFD results to meet the design requirements such as pressure loss and pattern factor. The combustor is fabricated using Ni-75 sheet of 1 mm thickness. A small combustor test facility is established. The combustor rig is tested for 50 Hours. The experimental results showed a blow-out phenomenon while the mass flow rate through the combustor is increased beyond a limit. Further through CFD analysis one of the cause for early blow out is identified to be a high mass flow rate through the swirler. The swirler area is partially blocked and many configurations are analysed. The optimum configuration is selected based on the flame position in the primary zone. The change in swirler area is implemented in the test model and further testing is carried out. The experimental results showed that the blow-out limit of the combustor is increased to a good extent. Hence the effect of swirler flow rate on recirculation zone length and flame blow out is also studied and presented. The experimental results showed that the pressure loss and pattern factor are in agreement with the design requirements.

Skylab's Astronaut Maneuvering Unit (Experiment M509) — A Comparison of Six Degree of Freedom Simulation and on-Orbit Flight

1974 ◽  
Vol 18 (2) ◽  
pp. 187-187
Author(s):  
A. M. Ray
Keyword(s):  
Space Shuttle ◽  
Space Station ◽  
Degree Of Freedom ◽  
Test Bed ◽  
Control Logic ◽  
Test And Evaluation ◽  
Unit Design ◽  
Design Requirements ◽  
Experiment Hardware ◽  
Six Degree Of Freedom

A test bed type astronaut maneuvering unit was designed and evaluated with the assistance of Martin Marietta's six degree of freedom simulator. Four different control modes were developed for this unit for test and evaluation inside Skylab's 22 foot diameter orbital workshop. The orbital tests have provided the experience and technology base necessary for space Shuttle and space station astronaut maneuvering unit design requirements. This paper is an overview of the M509 experiment hardware, procedures, and results with emphasis on the comparison between on-orbit test results and the six degree of freedom simulator. The simulator was used to develop the unit's design requirements, evaluate the control logic parameters, and for developing maneuvers and training the crew. The simulator will also be flown by the Skylab crews in May for post flight evaluation and simulator calibration. (Films of the simulations and on-orbit flight are available as part of this presentation.)

CTV: A New Method for Mapping a Full Scale Prototype of an Axial Compressor

1996 ◽  
Author(s):  
Vasco Mezzedimi ◽  
Pierluigi Nava ◽  
Dave Hamilla
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Theoretical Basis ◽  
Axial Compressor ◽  
Heavy Duty ◽  
Test Vehicle ◽  
Testing Method ◽  
Area Reduction ◽  
Speed Range ◽  
Compressor Inlet

The full mapping of a new gas turbine axial compressor at different speeds, IGV settings and pressure ratios (from choking to surge) has been performed utilizing a complete gas turbine with a suitable set of modifications. The main additions and modifications, necessary to transform the turbine into the Compressor Test Vehicle (CTV), are: - Compressor inlet throttling valve addition - Compressor discharge bleed valve addition - Turbine 1st stage nozzle area reduction - Starting engine change (increase in output and speed range). This method has been successfully employed on two different single shaft heavy-duty gas turbines (with a power rating of 11MW and 170 MW respectively). The paper describes the theoretical basis of this testing method and a specific application with the above mentioned 170 MW machine.

Twin Drive Gas Turbines in Single Proplusion Package for Norwegian Fast Patrol Boat

2009 ◽  
Author(s):  
Larry D. Davis ◽  
Are Soreng
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Rapid Change ◽  
New Techniques ◽  
Package Design ◽  
Left Hand ◽  
Package Size ◽  
System Maintenance ◽  
Design Requirements ◽  
Analytical Tools

The Royal Norwegian Navy, along with ship builder Umoe-Mandal, placed a requirement for two twin drive gas turbine packages (left hand/right hand) to fit into its existing Skjold Class fast patrol boat. Approximate output power was 16,000 HP, providing a vessel propulsion speed of over 60 knots. The design featured turbines of two different sizes: one PWC ST18 - 2680 HP and one PWC ST40 - 5365 HP. This combination proved optimal for the desired fighting ability, vessel range and reduced operating economies. The final COGAG (Combined Gas Turbine and Gas Turbine) configuration is the first of its type and may well have the highest horsepower-to-package size of any system designed to date. Many new techniques were developed to allow the propulsion packages to be assembled in place while providing the means for rapid change out of the gas turbines. The primary topics highlighted in this paper are: 1. Overview of key project and system design requirements. 2. Description of the final package design. 3. The concept development phase and review of the analytical tools used for design verification. 4. The integration and special design features required for incorporating twin turbines into a single package with requirements for single or both turbines operating. 5. The in place installation method and system maintenance of the package. 6. Program summary and testing to date.

Multidimensional Load Estimation Algorithms That Enable Performance Analysis of Industrial Gas Turbines Without A Priori Information

2008 ◽  
Vol 130 (4) ◽  
Author(s):  
Takuya Yoshida ◽  
Masaaki Bannai ◽  
Minoru Yoshida ◽  
Hiroyuki Yamada ◽  
Masaki Ishikawa
Keyword(s):  
Gas Turbines ◽  
A Priori ◽  
A Priori Information ◽  
Operating Data ◽  
Estimation Algorithms ◽  
Design Specifications ◽  
Performance Trends ◽  
Direct Modeling ◽  
Industrial Gas Turbines ◽  
Priori Information

Performance analysis and diagnosis for gas turbines usually assume the use of detailed design specifications or similar kinds of information for building and configuring engine models. This allows the nonlinearity of gas turbine performance characteristics to be taken into account. However, this approach tends to make it difficult for users of industrial gas turbines to analyze performance because (1) detailed design specifications are not necessarily supplied to the users, and (2) even if they were available, use of these kinds of information may often lead to complex procedures for model building and for making adjustments and configurations that all require high expertise. The purpose of this paper was to propose a direct modeling approach based only on operating data and not requiring a priori information like manufacturer-supplied specifications while preserving sufficient accuracy. The core element of this approach was the automatic identification and selection of base load operating data from various operating conditions. A set of load estimation algorithms was proposed. They were applied to 31,000h of operating data for two types of engines, which involved actual failure occurrences, and subsequent performance modeling and analysis were carried out. The following results were obtained. (1) The relative performance trends obtained revealed the quantitative extent of degradation during operation and of recovery by repair or engine change. (2) The performance trends gave a good account of actual failures. (3) The accuracy of the performance modeling measured by the 99th percentile of error was on the order of 1%. The proposed direct modeling approach offers sufficient accuracy to quantify the gradual degradation of performance and its recovery by maintenance. The performance trends obtained are useful for further fault diagnosis.

A Formal Approach to Specifications in Conceptual Design

1992 ◽  
Vol 114 (4) ◽  
pp. 659-666 ◽  
Author(s):  
A. Kusiak ◽  
E. Szczerbicki
Keyword(s):  
Artificial Intelligence ◽  
Key Words ◽  
Conceptual Design ◽  
Design Process ◽  
Formal Method ◽  
Functional Space ◽  
Synthesis Process ◽  
Formal Approach ◽  
Design Specifications ◽  
Design Requirements

In this paper, a methodology for the specification stage in conceptual design is presented. The specification stage provides requirements and transforms them into functions of the designed object. It occurs at the highest level of abstraction and it must provide enough information for the synthesis process where functions are transformed into design components that are further synthesized into the designed object. The proposed approach includes the following issues: specification of requirements, specification of functions, incorporation of logic into functional and requirement trees, representation of requirements-functions interaction, and optimization in the functional space. The methodology presented is illustrated with examples. Key words: design requirements, design specifications, conceptual design, design process, artificial intelligence, formal method

scholarly journals MS 9001F: A New Advanced Technology 50 Hz Gas Turbine

1990 ◽  
Author(s):  
D. E. Brandt ◽  
M. Colas
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Aircraft Engine ◽  
Advanced Technology ◽  
Test Plan ◽  
Heavy Duty ◽  
Compressor Inlet ◽  
Design Characteristics ◽  
Heavy Duty Gas Turbine

Following a thorough market analysis, the MS 9001F heavy duty gas turbine has been designed using aerodynamic scaling based on the 60 Hz MS 7001F. Effort put into the design has been shared by the engineering departments of ALSTHOM and GE. This paper discusses the market surveys for large heavy duty gas turbines as well as the basis of design for the MS 9001F, which has been derived from the MS 7001F. Specifically discussed are the role of scaling, the design characteristics of the MS 7001F and the MS 9001F, the results of 7001F prototype testing, the test plan for the MS 9001F, plant lay out possibilities and ratings. The MS 9001F gas turbine uses advanced aircraft engine technology in its design, with a rating based on a firing temperature of 1260°C (2300°F), which is 156°C (280°F) higher and with compressor inlet flow 50% greater than its predecessor, the MS 9001E.

Thrust Bearings for Power Gas Turbines

1971 ◽  
Author(s):  
A. J. Leopard
Keyword(s):  
Gas Turbines ◽  
Load Capacity ◽  
Point Of View ◽  
Power Losses ◽  
Service Experience ◽  
Thrust Bearings ◽  
Tilting Pad ◽  
Bearing Assembly ◽  
Design Requirements ◽  
New System

The design requirements of thrust bearings for power gas turbines are discussed with reference to designs which have given satisfactory service. The shortcomings of these designs are analyzed both from the point of view of efficiency and that of service experience. The development of a new system of lubrication designed to overcome these shortcomings is outlined. It is shown that this system, when applied to tilting pad thrust bearings in power turbines, can result in a simpler bearing assembly with increased load capacity and substantially ower power losses.

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