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Wyszukujesz frazę "blade seals" wg kryterium: Wszystkie pola


Wyświetlanie 1-7 z 7
Tytuł:
Research into flows in turbine blade seals. Part I: research methods
Autorzy:
Badur, J.
Kosowski, K.
Stępień, R.
Piwowarski, M.
Powiązania:
https://bibliotekanauki.pl/articles/1955758.pdf
Data publikacji:
2003
Wydawca:
Politechnika Gdańska
Tematy:
turbine seals
CFD calculations
experimental investigations
Opis:
Flows in the shroud clearance affect leakage losses and, thus, the turbine stage efficiency. However, at the same time, the distribution of pressure in the seal gaps plays an important role in the generation of the so-called "pressure forces", which may cause self-excited rotor vibrations of the aerodynamic type. Our investigations were carried out in order to show how a CFD code can cope with determining the pressure field in a rotor-blade shroud clearance. Experimental investigations of the pressure field in the shroud clearance were performed on a one-stage air model turbine of the impulse type. Measurements of pressure distribution were carried out for various rotor speeds and turbine loads. 3D calculations of flows in the model turbine were performed using the FLUENT CFD code. The calculations were carried out for the same variants which had been measured experimentally. In this part of the paper, the experimental stand and the numerical methods are described, while a detailed numerical analysis and a comparison between the experimental and the calculated results are presented in parts II and III, respectively.
Źródło:
TASK Quarterly. Scientific Bulletin of Academic Computer Centre in Gdansk; 2003, 7, 3; 309-317
1428-6394
Pojawia się w:
TASK Quarterly. Scientific Bulletin of Academic Computer Centre in Gdansk
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Research into flows in turbine blade seals. Part II: Numerical analysis
Autorzy:
Stępień, R.
Kosowski, K.
Badur, J.
Powiązania:
https://bibliotekanauki.pl/articles/1955751.pdf
Data publikacji:
2003
Wydawca:
Politechnika Gdańska
Tematy:
turbine seals
CFD calculations
experimental investigations
Opis:
3D calculations of an axial model turbine of the impulse type were performed using the FLUENT CFD code. The calculations were carried out for variants which had been measured experimentally. Special attention was paid to the pressure field in the rotor blade shroud clearance. The Multiple Reference Frame method, the Mixing Plane method and the Sliding Mesh method were applied, and meshes of different types and configurations were used for calculations. Only the Sliding Mesh technique appeared to describe non-stationary effects and pressure pulsations in the turbine flow channels and clearances. In this part of the paper, numerical analysis is described, while the comparison between the experimental and the calculated results is presented in part III.
Źródło:
TASK Quarterly. Scientific Bulletin of Academic Computer Centre in Gdansk; 2003, 7, 3; 319-327
1428-6394
Pojawia się w:
TASK Quarterly. Scientific Bulletin of Academic Computer Centre in Gdansk
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Research into flows in turbine blade seals. Part III: Numerical calculations versus experiment
Autorzy:
Kosowski, K.
Stępień, R.
Piwowarski, M.
Badur, J.
Powiązania:
https://bibliotekanauki.pl/articles/1955750.pdf
Data publikacji:
2003
Wydawca:
Politechnika Gdańska
Tematy:
turbine seals
CFD calculations
experimental investigations
Opis:
Experimental and theoretical investigations of the pressure field in the shroud clearance were performed on a one-stage air model turbine of the impulse type. Measurements of pressure distribution were carried out for various rotor speeds and turbine loads. 3D calculations of flows in this turbine were performed using the FLUENT CFD code. The calculations were carried out for variants which had been measured experimentally. The experimental data have been compared to theoretical results obtained with 3D codes for turbomachinery calculations. The Sliding Mesh and Multiple Reference methods have given very similar results of average values of pressure distribution and the velocity field in the shroud clearance. These results correspond to the experimental data. The pressure pulsations were determined only by the Sliding Mesh method, and these results have also been compared with the experiment. Stage flow calculations carried by the Sliding Mesh method with a structural shroud mesh and with a minimum number of 2-2.5 million cells have given a range of non-stationary pressure pulsations corresponding to the experimental data.
Źródło:
TASK Quarterly. Scientific Bulletin of Academic Computer Centre in Gdansk; 2003, 7, 3; 329-336
1428-6394
Pojawia się w:
TASK Quarterly. Scientific Bulletin of Academic Computer Centre in Gdansk
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Remarks on aerodynamic forces in seals of turbine stages
Autorzy:
Stępień, R.
Kosowski, K.
Powiązania:
https://bibliotekanauki.pl/articles/259359.pdf
Data publikacji:
2009
Wydawca:
Politechnika Gdańska. Wydział Inżynierii Mechanicznej i Okrętownictwa
Tematy:
rotor dynamics
self-excited vibrations
aerodynamic forces
blade seals
turbine shrouds
Opis:
This paper presents results of numerical examination of flow through over-shroud seals of turbine stages. Various labyrinth seals of different configurations and number of sealing teeth were considered. It was demonstrated that results of investigations of isolated seals cannot be directly used for analyzing turbine stage operation. Such approach may lead to relatively large errors in determining value of aerodynamic force and direction of its action.
Źródło:
Polish Maritime Research; 2009, S 1; 58-63
1233-2585
Pojawia się w:
Polish Maritime Research
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
On the modelling of aerodynamic force coefficients for over-shroud seals of turbine stages
Autorzy:
Włodarski, W.
Kosowski, K.
Powiązania:
https://bibliotekanauki.pl/articles/259389.pdf
Data publikacji:
2009
Wydawca:
Politechnika Gdańska. Wydział Inżynierii Mechanicznej i Okrętownictwa
Tematy:
rotor dynamics
self-excited vibrations
aerodynamic forces
blade seals
turbine shrouds
Opis:
This paper presents experimental investigations which made it possible to determine dynamic coefficients of labyrinth over-shroud seal of a model air turbine. The coefficients associate pressure forces with turbine rotor displacement, velocity and acceleration respective to turbine casing (linear model) and play important role in analyzing turbine-set dynamics. The obtained results indicated that involving serious errors can be expected in the case of application of the simplification consisting in neglecting inertia coefficients, proposed in the literature. It was simultaneously demonstrated that seals can be also met of weak damping qualities, for which to neglect damping coeffcients is allowable.
Źródło:
Polish Maritime Research; 2009, S 1; 71-74
1233-2585
Pojawia się w:
Polish Maritime Research
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Blade-type piston compressor investigation of seals
Autorzy:
Kalina, P.
Chomczyk, W.
Irzycki, A.
Snopkiewicz, K.
Powiązania:
https://bibliotekanauki.pl/articles/246203.pdf
Data publikacji:
2010
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
piston machines
piston compressor
seals testing
Opis:
The paper presents the test results of selected seals applied in the blade-type piston compressor designed and realized in Propulsion Department of Institute of Aviation according to Patent No 6822 specification. Principle of operation of the compressor and the construction of test stand utilized to the seals testing were presented in the paper published in the Journal of KONES 2009. The special blade-type piston realizes a pendulous movement in the circular cylinder divided into two bulkheads. Each of bulkheads, fitted out with a set of bidirectional operating valves, creates by sequential opening and closing of them two compression chambers for one blade. Comprehensive tests of different kinds of seals were carried out on a single-compression machine driven by pneumatic actuator. The pressure rise vs. blade movement and drop of pressure when the piston was stayed at top dead centre were measured. The results of leak tightness of other structures of blade-type piston were analyzed as well and are subject to the following paper. The new design of piston relied on fitting-out of piston with side disc was prepared with intention of eliminating the loss of usable pressure in compression chamber, especially in area of top dead centre. The proposed design eliminated the leaks on the drive shaft and lateral seals, but not on the cylindrical surface of disco.
Źródło:
Journal of KONES; 2010, 17, 1; 199-204
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Investigation of blade piston compressor
Autorzy:
Kalina, P.
Wodyński, P.
Irzycki, A.
Snopkiewicz, K.
Powiązania:
https://bibliotekanauki.pl/articles/245549.pdf
Data publikacji:
2011
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
mechanics
compressor
seals
Opis:
The paper presents the results of scientific research of the blade-type piston compressor which were conducted on the test rig built especially for this purpose. The construction concept of the compressor, design calculation of its main elements and tests of contact- and contactless sealing types were discussed in papers published at subsequent KONES-symposia 2009 and 2010. The results shown in present document are focused on studies of compressor having the piston equipped with labyrinth or contact seals. When testing on test bench, the intake air flow to the compressor as well as temperature and pressure of air compressed in the tank of 0.1 m3 were measured. Quick-changing pressure in the compression chamber and air temperature at the compressor's outlet were recorded and analyzed, also. The research was carried out for contact-type seals made of various materials which do not require lubrication and for contactless-type seals (labyrinth). In the course of studies the proper backlash between the piston and the cylinder wall was matched to ensure trouble-free operation of installation. The results of compressor power demand were presented in this article, too. This research work is performed under the framework program "Inicjatywa Technologiczna I" No 12218.
Źródło:
Journal of KONES; 2011, 18, 3; 143-148
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
    Wyświetlanie 1-7 z 7

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