Temat: axial flow compressor - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: A blade design performance based off-design loss prediction method for axial flow compressors and cascades
Autorzy:: Wu, Dongrun
Teng, Jinfang
Qiang, Xiaoqing
Yang, Zhong
Powiązania:: https://bibliotekanauki.pl/articles/281416.pdf
Data publikacji:: 2019
Wydawca:: Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
Tematy:: blade design performance
off-design loss
prediction method
axial flow compressor
cascade
Opis:: A series of compressor and cascade test recordings are studied to investigate the off-design loss prediction method. The blade design performance is used to predict the off-design loss changing rate at all operating conditions through analytical derivations and statistical correlation studies. The linear correlation between the incidence and a non-dimensional blade loading factor is the foundation of the prediction method. The off-design incidence is normalized using the off-design blade loading factor for different series of blade designs. An analytical method is introduced to predict the off-design blade loading factor based on design parameters and linear correlation. The changing rate of the off-design loss against the blade loading factor is empirically given through statistical analysis. In application, the prediction method can be used to demonstrate the design space of the off-design incidence for a blade series. The modification of the endwall and the rotor tip loss is recommended to give a more accurate prediction in those regions.
Źródło:: Journal of Theoretical and Applied Mechanics; 2019, 57, 4; 973-985
1429-2955
Pojawia się w:: Journal of Theoretical and Applied Mechanics
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: CFD code - a useful tool for the turbomachinery designer
Autorzy:: Chodkiewicz, R.
Sobczak, K.
Papierski, A.
Borzecki, T.
Powiązania:: https://bibliotekanauki.pl/articles/1931600.pdf
Data publikacji:: 2002
Wydawca:: Politechnika Gdańska
Tematy:: CFD
radial compressor
radial pump
axial flow turbine
Opis:: The presentation of CFX-TASCflow code possibilities for the turbomachinery design is the main aim of this study. In the first part of the work the compressor design process is presented. Next, CFX-TASCflow possibilities in predicting unstable operating conditions (surge) are shown. The one-stage, radial blower installed in the Institute of Turbomachinery TU of Lodz has been chosen owing to the available numerous experimental data. The pump calculations discussed in the third part concern a comparison of different turbulence models with the experimental results. In the last part devoted to the turbine design, the code usefulness is proved on the examples of the last stage design process.
Źródło:: TASK Quarterly. Scientific Bulletin of Academic Computer Centre in Gdansk; 2002, 6, 4; 553-575
1428-6394
Pojawia się w:: TASK Quarterly. Scientific Bulletin of Academic Computer Centre in Gdansk
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Estymacja punktu pracy sprężarki i jego parametrów w oparciu o charakterystyki sprężarek
Estimating the compressors works point and its parameters based on performance of compressors
Autorzy:: Kozakiewicz, A.
Powiązania:: https://bibliotekanauki.pl/articles/212550.pdf
Data publikacji:: 2016
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: sprężarka osiowa
opływ palisady sprężarki
pompaż
turbinowe silniki odrzutowe
axial compressor
flow around grid of blades
surge
turbine jet engine
Opis:: W artykule przedstawiono problematykę związaną z estymacją punktu pracy sprężarki w oparciu ojej charakterystykę. Analizowano problematykę związaną z pracą poszczególnych stopni zespołu ze względu zmiany kąta natarcia strumienia w wyniku zmian prędkości obrotowych. Przedstawiono wyniki analizy numerycznej opływu stopnia sprężarki. Zanalizowano zmianę położenia linii pracy silnika w wyniku wyboru kąta natarcia na zakresie obliczeniowym. Zaprezentowano problematykę ze zmianą warunków pracy poszczególnych stopni sprężarki.
This paper presents problems concerning the estimation of the point works of the compressor and its parameters based on its characteristics. Problems connected with the work of individual compressor stages regarding the change of the angle of attack stream as a result of changes in rotating velocities were analysed Results of the numerical analysis of the stage compressor's round flow were demonstrated. The- dislocation of the work line of the engine as a result of the choice of the angle of attack on the computational range were presented. Problems with modifying work conditions for individual compressor stages were presented.
Źródło:: Prace Instytutu Lotnictwa; 2016, 3 (244); 363-372
0509-6669
2300-5408
Pojawia się w:: Prace Instytutu Lotnictwa
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Multiple spike stall cells in low speed axial compressor rotor blade row
Autorzy:: Taghavi-Zenouz, R
Abbasi, S.
Powiązania:: https://bibliotekanauki.pl/articles/279770.pdf
Data publikacji:: 2015
Wydawca:: Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
Tematy:: axial compressor
spike stall inception
tip leakage flow
frequency spectrum
Opis:: Inception and development of multiple stall cells of short length scales are numerically investigated in an axial compressor rotor blade row. The method of investigation is based on time accurate three-dimensional full annulus simulations. Time dependent flow structure results revealed that there are two criteria responsible for inception of a special kind of stall, introduced as spike stall in the literature. These criteria are defined as leading edge spillage and trailing edge backflow, which occur at specific mass flow rates near to stall conditions. The numerical results revealed that once the spike stall cells appear, they cover roughly two blade passages in the circumferential direction and cover about 25% of the blade height. By further revolution of the blade row, the number of cells tends to increase. For the present case study, the number of stall cells increased to three after 8.5 rotor revolutions from the moment of the initial spike stall occurrence. Even at this moment, both of the above mentioned criteria for the spike stall inception have been observed within the blades passages. These events caused the inlet relative flow angle to the blade rows, and therefore the flow incidence angle and consequent blockage to the main flow, to increase. The tip leakage flow frequency spectrum has been studied through surveying instantaneous static pressure signals imposed on pressure side of the blades and also on the casing walls. These latter results showed that any further revolving of the rotor blade row, exceeding 8.5 revolutions, causes the spike stall to disturb the flow structure significantly.
Źródło:: Journal of Theoretical and Applied Mechanics; 2015, 53, 1; 47-57
1429-2955
Pojawia się w:: Journal of Theoretical and Applied Mechanics
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: Numerical loss analysis on slot-type casing treatment in a transonic compressor stage
Autorzy:: Zhu, M.-M.
Qiang, X.-Q.
Teng, J.-F.
Powiązania:: https://bibliotekanauki.pl/articles/280437.pdf
Data publikacji:: 2017
Wydawca:: Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
Tematy:: axial compressor
numerical simulation
slot-type casing treatment
loss mechanism
tip leakage flow
Opis:: To understand the loss mechanism of slot-type casing treatment, a numerical loss analysis has been carried out in a 1.5 axial transonic compressor stage with various slots. Spanwise and streamwise distribution curves of pitch-averaged entropy have been presented to survey the development of loss generation. Further, detailed entropy distributions at eight axial cuts, which have been taken through the blade row and slots, have been further analyzed to interpret the loss mechanism. The most dramatic loss growth occurred above 95% span, which directly resulted from slots injection flow upstream the leading edge. Loss generations with smooth casing have been primarily ascribed to low-momentum tip leakage flow/vortex and suction surface separation at the leading edge. CU0 slot, the arc-curved slots with 50% rotor tip exposure, has been capable of suppressing the suction surface separation loss. Meanwhile, accelerated tip leakage flow brought about additional loss near the casing and pressure surface. Upstream high entropy flow would be absorbed into the rear portion of slots repeatedly, which resulted in further loss.
Źródło:: Journal of Theoretical and Applied Mechanics; 2017, 55, 1; 293-306
1429-2955
Pojawia się w:: Journal of Theoretical and Applied Mechanics
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: Numerical study of stall inception in a transonic axial compressor rotor based on the throttle model
Autorzy:: Zhu, X.
Liu, B.
Hu, J.
Shen, X.
Powiązania:: https://bibliotekanauki.pl/articles/280516.pdf
Data publikacji:: 2015
Wydawca:: Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
Tematy:: stall
axial compressor
throttle
tip clearance flow
Opis:: The goal of the current paper is to investigate inner flow behavior on stall inception in a transonic compressor rotor. The stall inception process is numerically carried out by unsteady 3-D simulations based on the throttle model. The current study shows that stall starts from the tip of the blade, and stall cell extends to the axial, circumferential and radial directions. Through the comparison of flow transition characteristics at different flow rate conditions, the interface between the incoming flow and tip clearance flow shifts forward to the upstream as the mass flow decreases. Eventually, the shock detaches from the blade leading edge, and tip clearance flow spills into the adjacent blade passage, thus stall happens in the affected blade passages.
Źródło:: Journal of Theoretical and Applied Mechanics; 2015, 53, 2; 307-316
1429-2955
Pojawia się w:: Journal of Theoretical and Applied Mechanics
Dostawca treści:: Biblioteka Nauki

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