Validation of MISES 2 D Boundary Layer Code for High Pressure Turbine Aerodynamic Design

Date

2007-01-01

Author

ANDREW, PHILIP
Kahveci, Harika Senem

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

255
views

0
downloads

Avoiding aerodynamic separation and excessive shock losses in gas turbine turbomachinery components can reduce fuel usage, and thus reduce operating cost. In order to achieve this, blading designs should be made robust to a wide range of operating conditions. Consequently, a design tool is needed which can be executed quickly for each of many operating conditions, and on each of several design sections which will accurately capture loss, turning and loading. This paper presents the validation of a boundary layer code, MISES, versus experimental data from a 2-D linear cascade approximating the performance of a moderately-loaded, mid-pitch section from a modern aircraft high-pressure turbine [1-2]. The validation versus measured loading, turning, and total pressure loss is presented for a range of exit Mach numbers from approximate to 0.5 to 1.2, and across a range of incidence from -10 degrees to +14.5 degrees relative to design incidence.

Subject Keywords

CFD, Loss, Incidence,, HPT, Off-design, Transonic, 2-D cascade, Boundary layer method, MISES, Validation

URI

https://hdl.handle.net/11511/35848

DOI

https://doi.org/10.1115/gt2007-28123

Collections

Department of Aerospace Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

Validation of MISES Two-Dimensional Boundary Layer Code for High-Pressure Turbine Aerodynamic Design ANDREW, PHILIP; Kahveci, Harika Senem (ASME International, 2009-07-01) Avoiding aerodynamic separation and excessive shock losses in gas turbine turbomachinery components can reduce fuel usage and thus reduce operating cost. In order to achieve this, blading designs should be made robust to a wide range of operating conditions. Consequently, a design tool is needed-one that can be executed quickly for each of many operating conditions and on each of several design sections, which will accurately capture loss, turning, and loading. This paper presents the validation of a bounda...
Application of structural modification method to nonlinear vibration analysis of bladed disks Şayin, Burcu; Ciğeroğlu, Ender; Department of Mechanical Engineering (2013) High cycle fatigue failure of turbine blades is one of the most important problems in the design of gas turbine engines; hence, bladed-disk assemblies have been studied extensively for more than half a century. Damping design becomes an important issue in order to attenuate the blade vibration. For bladed-disk systems, friction damping concept is a common strategy to decrease vibration levels. There are different strategies in order to add friction damping to the system: blade-to-blade dampers such as shrou...
APPLICATION OF A FUZZY LOGIC CONTROLLER FOR SPEED CONTROL ON A SMALL-SCALE TURBOJET ENGINE Usenmez, Serdar; Ekinci, Sinan; Uzol, Oğuz; Yavrucuk, İlkay (2014-06-20) Having a small-scale turbojet engine operate at a desired speed with minimum steady state error, while maintaining good transient response is crucial in many applications, such as UAVs, and requires precise control of the fuel flow.
Development and evaluation of new bleed boundary condition models for supersonic inlet boundary layer bleed flow Akar, Gökhan; Eyi, Sinan; Department of Aerospace Engineering (2019) Shock wave/boundary layer interaction is an important issue that should be considered when studying supersonic inlet design for air vehicles. Porous bleed systems have traditionally been used for increase stability and efficiency of the supersonic inlets by means of removing the lower momentum part of the boundary layer to prevent flow separation caused by adverse pressure gradient. However, evaluating and determining the effect of the boundary layer bleed system on the performance of the supersonic inlet i...
Modeling the effect of SCR denox unit on diesel engine performance Pelen, Pelsu; Kazanç Özerinç, Feyza; Department of Mechanical Engineering (2020) The design of the internal combustion engines and the aftertreatment systems cannot be considered independently since imposing an aftertreatment equipment into the exhaust system brings extra backpressure which in turn decreases the engine efficiency and increases the fuel consumption and CO2 emission. In the present study, the existing 3D monolith reactor model in COMSOL Multiphysics® applications is modified to account for an SCR deNOx unit having 600 cpsi cell density by using exhaust mass flow rate and ...

Citation Formats

P. ANDREW and H. S. Kahveci, “Validation of MISES 2 D Boundary Layer Code for High Pressure Turbine Aerodynamic Design,” 2007, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/35848.