scholarly journals Design, analysis and testing of a radial-axial hybrid active force compliant tool head for deburring turbine engine parts

2021 ◽  
Author(s):  
Brian A. Petz
Keyword(s):  
Magnetic Field ◽  
Gas Turbine ◽  
Design Process ◽  
Burr Formation ◽  
Active Force ◽  
Axial Motion ◽  
Turbine Engine ◽  
Magnetic Field Sensors ◽  
Radial System ◽  
Motion System

In this thesis, a new concept and design is presented for a tool with the purpose of deburring gas turbine engine parts. This new concept utilizes both axial and radial active force compliance to accomplish the burr removal in a more robust manner. The axial and radial components are integrated in a manner that allows them to be decoupled, reducing the complexity of the system. The tool is designed around a pneumatic spindle that is affixed to pneumatic axial actuators. The axial motion system is then affixed to the radial system which makes use of a 2 axis rotary gimbal, acting as a 2-D pivot. Sensors for the axial and radial components of the tool are independent of each other. Axial sensing is accomplished using a commercial string-potentiometer and radial sensing is accomplished using magnets and magnetic field sensors. Burr formation and methods of removal are discussed. Different deburring tool designs available commercially and through literature are then explored. The design process of selecting axial and radial actuation and sensing and integrating them together while keeping the systems decoupled is outlined. Modeling of the tool is then developed and a simulation of the tool is presented to illustrate the deburring mechanics of the decoupled axial and radial components. Experimentation to determine the stiffness qualities of the tool as well as calibration of the sensors are presented and used within the simulation.

scholarly journals Design, analysis and testing of a radial-axial hybrid active force compliant tool head for deburring turbine engine parts

2021 ◽  
Author(s):  
Brian A. Petz
Keyword(s):  
Magnetic Field ◽  
Gas Turbine ◽  
Design Process ◽  
Burr Formation ◽  
Active Force ◽  
Axial Motion ◽  
Turbine Engine ◽  
Magnetic Field Sensors ◽  
Radial System ◽  
Motion System

In this thesis, a new concept and design is presented for a tool with the purpose of deburring gas turbine engine parts. This new concept utilizes both axial and radial active force compliance to accomplish the burr removal in a more robust manner. The axial and radial components are integrated in a manner that allows them to be decoupled, reducing the complexity of the system. The tool is designed around a pneumatic spindle that is affixed to pneumatic axial actuators. The axial motion system is then affixed to the radial system which makes use of a 2 axis rotary gimbal, acting as a 2-D pivot. Sensors for the axial and radial components of the tool are independent of each other. Axial sensing is accomplished using a commercial string-potentiometer and radial sensing is accomplished using magnets and magnetic field sensors. Burr formation and methods of removal are discussed. Different deburring tool designs available commercially and through literature are then explored. The design process of selecting axial and radial actuation and sensing and integrating them together while keeping the systems decoupled is outlined. Modeling of the tool is then developed and a simulation of the tool is presented to illustrate the deburring mechanics of the decoupled axial and radial components. Experimentation to determine the stiffness qualities of the tool as well as calibration of the sensors are presented and used within the simulation.

scholarly journals Simple Design Methods for the Prediction of Radial Static Pressure Distributions in a Rotor-Stator Cavity With Radial Inflow

1995 ◽  
Author(s):  
Kenneth J. Hart ◽  
Alan B. Turner
Keyword(s):  
Gas Turbine ◽  
Design Process ◽  
Static Pressure ◽  
Tangential Velocity ◽  
Operating Conditions ◽  
Simple Design ◽  
Turbine Engine ◽  
Static Pressure Distribution ◽  
Variable Quantity ◽  
Wide Range

Research has been conducted into the effects of component geometry and air bleed flow on the radial variation of static pressure and core tangential velocity in a rotor-stator cavity of the type often found behind the impeller of a gas turbine engine centrifugal compressor. A CFD code, validated by rig test data for a wide range of rotor-stator axial gaps and throughflows, has been used to generate pressure and velocity data for typical gas turbine operating conditions. This data has been arranged as a series of simple design curves which relate the rotational speed of the core of fluid between rotor and stator boundary layers, and hence the static pressure distribution, to primary cavity geometry, rotational Reynolds number and bleed throughflow with particular attention to radial inflowing bleeds. Details are provided on the use and limitations of these curves. Predictions using this method have been compared successfully with measured data from engine test and a compressor test rig, modified to facilitate variable quantity and direction of impeller rear face bleed flow, at typical gas turbine operational power conditions. Data generated by these curves can be used directly in the design process and to validate integral momentum methods which can provide relatively simple computation of rotor-stator cavity pressure and velocity distributions independently or within air system network programs. This approach is considered to be a cost and time effective addition to the analytical design process especially if validated CFD code, which can accommodate rotational flows consistently and accurately, is not available.

Virtual Gas Turbine: Pre-Processing and Numerical Simulations

2016 ◽  
Author(s):  
Feng Wang ◽  
Mauro Carnevale ◽  
Gan Lu ◽  
Luca di Mare ◽  
Davendu Kulkarni
Keyword(s):  
Computational Model ◽  
Numerical Simulations ◽  
Gas Turbine ◽  
Design Process ◽  
Large Scale ◽  
Physical Phenomenon ◽  
Navier Stokes ◽  
Time Cost ◽  
Turbine Engine ◽  
Geometrical Shapes

The design process of a gas turbine engine involves interrelated multi-disciplinary and multi-fidelity designs of engine components. Traditional component-based design process is not always able to capture the complicated physical phenomenon caused by component interactions. It is likely that such interactions are not resolved until hardware is built and tests are conducted. Component interactions can be captured by assembling all these components into one computational model. Nowadays, numerical solvers are fairly easy to use and the most time-consuming (in terms of man-hours) step for large scale gas turbine simulations is the preprocessing process. In this paper, a method is proposed to reduce its time-cost and make large scale gas turbine numerical simulations affordable in the design process. The method is based on a novel featured-based in-house geometry database. It allows the meshing modules to not only extract geometrical shapes of a computational model and additional attributes attached to the geometrical shapes as well, such as rotational frames, boundary types, materials, etc. This will considerably reduce the time-cost in setting up the boundary conditions for the models in a correct and consistent manner. Furthermore, since all the geometrical modules access to the same geometrical database, geometrical consistency is satisfied implicitly. This will remove the time-consuming process of checking possible mismatching in geometrical models when many components are present. The capability of the proposed method is demonstrated by meshing the whole gas path of a modern three-shaft engine and the Reynold’s Averaged Navier-Stokes (RANS) simulation of the whole gas path.

Integration of Multi-Disciplinary Factors Into Turbine Cooling Design

2001 ◽  
Author(s):  
Boris Glezer
Keyword(s):  
Gas Turbine ◽  
Design Process ◽  
Early Phase ◽  
Engine Performance ◽  
Gas Turbine Engine ◽  
Support Structures ◽  
Turbine Engine ◽  
Turbine Cooling ◽  
Cooling Design ◽  
Blade Tip

The presented paper describes a multi-disciplinary cooling selection practice applied to major gas turbine engine hot section components, including turbine nozzles, blades, discs, combustors and support structures maintaining blade tip clearances. The paper demonstrates the benefits of close interaction between participating disciplines, when this interaction starts in the early phase of the hot section development. The approach targets advances in engine performance and cost by optimizing the design process, often requiring compromises within individual disciplines.

Flexible manufacturing in repair of gas turbine engine components

1992 ◽  
Author(s):  
KIRK D ◽  
ANDREW VAVRECK ◽  
ERIC LITTLE ◽  
LESLIE JOHNSON ◽  
BRETT SAYLOR
Keyword(s):  
Gas Turbine ◽  
Flexible Manufacturing ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Engine Components
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