Temat: turbine cooling - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Preliminary analysis of thermodynamic cycle of turbofan engine fuelled by hydrogen
Autorzy:: Marszalek, N.
Powiązania:: https://bibliotekanauki.pl/articles/247482.pdf
Data publikacji:: 2018
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: liquid hydrogen
turbofan engine
turbine cooling
engine thermodynamic cycle
engine performance
Opis:: Presented article is focus on analysis of the effect of hydrogen fuel on turbofan engine performance. Selected properties of hydrogen and possibility of introduction in civil aviation were discussed. Hydrogen implementation as aviation fuel offers obvious advantages such as low emission of combustion product, higher payload, lower fuel consumption, general availability but also poses great technical challenges. The most important aspect is to ensure engine operational safety at very high level. Hydrogen implementation would eliminate the aviation dependence of exhausting sources of fossil fuels especially of crude oil. The thermodynamic model of turbofan engine was implemented in MATLAB environment. Accepted assumptions have been discussed. Turbine cooling process has been included in the numerical model. Working fluid was modelled as semi-perfect gas. Analysis was carried out for take-off and design point conditions. Engine performances were compared for two kinds of applied fuels: liquid hydrogen and commonly used in turbine engines kerosene. Combustion heat of hydrogen is about three time higher than in comparison with conventional turbine engine fuel, what exert significant influence on engine performance. The results of engine thermodynamic cycle analysis indicate the increase in specific thrust and significant reduction of specific fuel consumption. The results are presented in tabular form and on the graphs. Obtained results have been discussed and the direction of further research was indicated.
Źródło:: Journal of KONES; 2018, 25, 3; 347-354
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Maximisation of Combined Cycle Power Plant Efficiency
Maksymalizacja sprawności elektrowni gazowo-parowych
Autorzy:: Kotowicz, J.
Job, M.
Brzęczek, M.
Powiązania:: https://bibliotekanauki.pl/articles/397508.pdf
Data publikacji:: 2015
Wydawca:: ENERGA
Tematy:: combined cycle power plant
turbine cooling
thermodynamic optimisation
elektrownia gazowo-parowa
chłodzenie turbiny
optymalizacja
Opis:: The paper presents concepts for increasing the efficiency of a modern combined cycle power plant. Improvement of gas turbine performance indicators as well as recovering heat from the air cooling the gas turbine’s flow system enable reaching gross electrical efficiencies of around 65%. Analyses for a wide range of compressor pressure ratios were performed. Operating characteristics were developed for the analysed combined cycle plant, for different types of open air cooling arrangements of the gas turbine’s expander: convective, transpiration and film.
W artykule przedstawiono koncepcje zwiększenia sprawności nowoczesnej elektrowni gazowo-parowej. Poprawa charakterystyk pracy turbiny gazowej oraz wykorzystanie ciepła powietrza chłodzącego układ przepływowy turbiny gazowej pozwalają na osiągnięcie sprawności elektrycznej brutto rzędu 65%. Analizy przeprowadzono w szerokim zakresie stopni sprężania w kompresorze. Sporządzono główne charakterystyki pracy analizowanego układu gazowo-parowego dla różnych typów chłodzenia otwartego powietrzem ekspandera turbiny gazowej: konwekcyjnego, transpiracyjnego oraz błonowego.
Źródło:: Acta Energetica; 2015, 4; 42-53
2300-3022
Pojawia się w:: Acta Energetica
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Modeling and analysis of jet engine with cooling turbine
Autorzy:: Jakubowski, R.
Powiązania:: https://bibliotekanauki.pl/articles/247838.pdf
Data publikacji:: 2012
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: jet engine
modelling of jet engine
modelling of jet engine with cooling turbine
Opis:: The problems of the turbojet engines with a cooling turbine modelling are discussed in the paper. The cooling systems of the contemporary jet engines are briefly described in the first part of the paper. Than the models of various turbine, cooling systems are presented and discussed. The main scope of the paper is the turbine cooling system consisted of internal convection cooling and external film cooling of turbine blades. This cooling system is commonly used in contemporary military and civil turbojet engines. The model of the internal-external cooling turbine incorporated in the overall jet engine model is presented and discussed. Some simplifying assumptions are discussed. Then the results of the jet engine calculation taking into account the proposed model are presented in the tables. The results are compared with results obtained by simple model of the jet engine with cooling turbine. The simple model is commonly applied for 1D turbojet engine analysis. Based on this analysis, some aspects of the turbojet engine calculation with reference to different models applied for description of the turbine cooling process are presented and discussed. The analysis allowed formulating some conclusions, which are presented in the final part of the paper. One of them is that proposed model of cooling turbine allows to calculate of coolant mass flow, while the simple models of cooling turbine require the assumption of coolant mass. By this way the calculation results accuracy by the use of simple model, strictly depend on the proper assumption of coolant mass flow.
Źródło:: Journal of KONES; 2012, 19, 2; 235-243
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Numerical simulation of thermally loaded aircraft engine turbine blade covered with thermal barrier coating - TBC
Autorzy:: Łazarczyk, M.
Domański, R.
Powiązania:: https://bibliotekanauki.pl/articles/246553.pdf
Data publikacji:: 2012
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aircraft engines
turbine
TBC
coating
blade cooling
Opis:: The objective of this thesis is to present the impact of the turbine blade cooling on blade material temperature as well as to assess advantages and disadvantages of applied cooling method (TBC coating combined with internal cooling). To calculate the conjugated heat transfer analysis generating 3d model and mesh of the blade and its cooling was required. Model mesh was covered with boundary layer in order to properly simulate conditions near the blade walls and obtain accurate results. Calculated blade was put in the canal simulating hot combustion gasses flow. Geometry of model described above was created using Unigraphics NX5 program based on drawings obtained from available literature, and data acquired from the Internet. The discretization was done in commercial pre--processor GAMBITŽ. Conjugated heat transfer analysis was conducted in program FLUENTŽ for two different cases, where the TBC material properties were changed. The goal of this thesis was to obtain temperature fields and distribution in the turbine blade airfoil and to evaluate if applied cooling is sufficient to cool down this thermally loaded part of the engine. Calculated results show that proposed blade heat protection with TBC and internal cooling canal is insufficient during steady state condition, especially on the blade leading and trailing edge. In these two locations, the TBC coating is overheated, and the high temperature level of blade material is unacceptable for materials used in jet engine turbine industry.
Źródło:: Journal of KONES; 2012, 19, 3; 271-277
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: Numerical study of the ejection cooling mechanism of ventilation for a marine gas turbine enclosure
Autorzy:: Shi, Hong
Zhang, Qianwei
Liu, Meinan
Yang, Kaijie
Yuan, Jie
Powiązania:: https://bibliotekanauki.pl/articles/32908258.pdf
Data publikacji:: 2022
Wydawca:: Politechnika Gdańska. Wydział Inżynierii Mechanicznej i Okrętownictwa
Tematy:: gas turbine enclosure
ejecting cooling
ventilation
CFD
Opis:: A marine gas turbine enclosure must be designed to prevent overheating of the electrical and engine control components as well as diluting potential fuel leaks. In order to achieve an optimal enclosure design, a numerical study of the ventilation-ejection cooling mechanism of a gas turbine enclosure is carried out in this paper. The evaluation index of the ejection cooling performance is first proposed and the algorithm of numerical simulation is verified. On this basis, orthogonal combinations of structural parameters are carried out for the expansion angle α of the lobed nozzle and the spacing S between the outlet plane of the lobed nozzle and the inlet plane of the mixing tube. The flow and the temperature distribution inside the enclosure are analysed under different operating conditions. The results show that the influence of the lobed nozzle expansion angle α and the spacing S on the performance is not a single-valued function but the two influencing factors are mutually constrained and influenced by each other. For any spacing, the combined coefficient is optimal for the expansion angle α = 30°. When the expansion angle α = 45° and the spacing S = 100 mm, the combined coefficient and the temperature distribution inside the enclosure are optimal at the same time.
Źródło:: Polish Maritime Research; 2022, 3; 119-127
1233-2585
Pojawia się w:: Polish Maritime Research
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: Aerodynamic enhancement in inner channel of turbine blade
Autorzy:: Kaczyński, P.
Szwaba, R.
Puchowski, B.
Doerffer, P.
Flaszyński, P.
Powiązania:: https://bibliotekanauki.pl/articles/1938640.pdf
Data publikacji:: 2015
Wydawca:: Politechnika Gdańska
Tematy:: turbine blade
internal channel
radial passage
blade cooling
Opis:: This paper presents the numerical and experimental study of the flow structure in a radial cooling passage model of a gas turbine blade. The investigations focus on the flow aerodynamics in the channel, which is an accurate representation of the configuration used in aero engines. The flow structure and pressure drop were measured by classical measurement techniques. The stagnation pressure and velocity measurements in a channel outlet plane were performed. The investigations concerning the flow field and heat transfer used in the design of radial cooling passages are often developed from simplified models. It is important to note that real engine passages do not have perfect rectangular cross sections, but include corner fillets, ribs with fillet radii and special orientation. Therefore, this work provides detailed fluid flow data for a model of radial cooling geometry which possesses very realistic features. The main purpose of these investigations was to study different channel configurations and their influence on the flow structure and pressure losses in a radial cooling passage of a gas turbine blade.
Źródło:: TASK Quarterly. Scientific Bulletin of Academic Computer Centre in Gdansk; 2015, 19, 2; 101-110
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: 7.

Tytuł:: Heat transfer coefficient measurements on curved surfaces
Autorzy:: Kurowski, Marcin
Powiązania:: https://bibliotekanauki.pl/articles/1845471.pdf
Data publikacji:: 2021
Wydawca:: Polska Akademia Nauk. Czytelnia Czasopism PAN
Tematy:: heat transfer coefficient
measurements
methodology
gas turbine
cooling
Opis:: This paper presents the results of experimental research on heat transfer distribution under the impinging jets at high jet velocity on curved surfaces. The air jets flow out from the common pipe and impinge on a surface which is cooled by them, in this way all together create a model of external cooling system of low pressure gas turbine casing. Preliminary measurement results from the flat plate case were compared with the results from the curved surface case. Surface modification presented in this paper relied on geometry change of flat surface to the form of a ‘bump’. The special system of pivoted mirrors was implemented during the measurements to capture the heat exchange on curved surfaces of the bump. The higher values of mean heat transfer coefficient were observed for all flow cases with a bump in relation to the reference flow case with a flat plate.
Źródło:: Archives of Thermodynamics; 2021, 42, 2; 155-170
1231-0956
2083-6023
Pojawia się w:: Archives of Thermodynamics
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 8.

Tytuł:: Turbine stage expansion model including internal air film cooling and novel method of calculating theoretical power of a cooled stage
Autorzy:: Trawiński, Paweł
Powiązania:: https://bibliotekanauki.pl/articles/2134930.pdf
Data publikacji:: 2022
Wydawca:: Polska Akademia Nauk. Czytelnia Czasopism PAN
Tematy:: gas turbine
expansion line
air film cooling
theoretical stage power
Opis:: Systematic attempts to maximise the efficiency of gas turbine units are achieved, among other possibilities, by increasing the temperature at the inlet to the expansion section. This requires additional technological solutions in advanced systems for cooling the blade rows with air extracted from the compressor section. This paper introduces a new mathematical model describing the expansion process of the working medium in the turbine stage with air film cooling. The model includes temperature and pressure losses caused by the mixing of cooling air in the path of hot exhaust gases. The improvement of the accuracy of the expansion process mathematical description, compared with the currently used models, is achieved by introducing an additional empirical coefficient estimating the distribution of the cooling air along the profile of the turbine blade. The new approach to determine the theoretical power of a cooled turbine stage is also presented. The model is based on the application of three conservation laws: mass, energy and momentum. The advantage of the proposed approach is the inclusion of variable thermodynamic parameters of the cooling medium. The results were compared with the simplified models used in the literature: separate Hartsel expansion, mainstream pressure, weighted-average pressure and fully reversible. The proposed model for expansion and the determination of theoretical power allows for accurate modelling of the performance of a cooled turbine stage under varying conditions.
Źródło:: Archives of Thermodynamics; 2022, 43, 3; 3--27
1231-0956
2083-6023
Pojawia się w:: Archives of Thermodynamics
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 9.

Tytuł:: Gas turbine direct exhaust gas integration in process industry – review of applications and opportunities for polish market
Autorzy:: Cichocki, Marek
Salamonik, Ilona
Bielecki, Marcin
Fadlun, Ever
Rusowicz, Artur
Powiązania:: https://bibliotekanauki.pl/articles/111073.pdf
Data publikacji:: 2020
Wydawca:: Centrum Rzeczoznawstwa Budowlanego Sp. z o.o.
Tematy:: turbine exhaust gases
gas turbines
utilization
direct drying
cooling
heating
Opis:: The typical combined heat and power plants requires the introduction of additional heating medium. The alternative solution is the direct integration of the exhaust gases from heat engine. The high temperature, surplus oxygen and low water content of the GTs exhaust gases enabled the successful integration at industrial scale as: preheated combustion air for industrial furnaces, heat source for drying and for absorption chillers. The article comprises the reference list for direct exhaust gas integration of GTs produced by GE, the processes overview, GTs selection criteria, as well as the review of documented GTs applications in process industry focusing on technical and economic considerations. The described solutions allowed to reduce the specific energy consumption in the range from 7 to 20% or the costs of energy consumption by 15-30%. The overall efficiency of cogeneration plant above 90% was achieved. The preliminary assessment of potential applications for GTs produced by GE with TEG integration in Polish process industry is done.
Źródło:: Inżynieria Bezpieczeństwa Obiektów Antropogenicznych; 2020, 1; 1-18
2450-1859
2450-8721
Pojawia się w:: Inżynieria Bezpieczeństwa Obiektów Antropogenicznych
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 10.

Tytuł:: Analiza obciążeń cieplnych podczas rozruchu nadkrytycznych turbin parowych z chłodzeniem zewnętrznym
Analysis of thermal loads during start-up in supercritical steam turbines with external cooling
Autorzy:: Kosman, W.
Powiązania:: https://bibliotekanauki.pl/articles/173013.pdf
Data publikacji:: 2013
Wydawca:: Polska Akademia Nauk. Czytelnia Czasopism PAN
Tematy:: obciążenie cieplne
turbina parowa
chłodzenie zewnętrzne
system chłodzenia
thermal load
steam turbine
external cooling
cooling system
Opis:: Rozruch turbiny parowej wiąże się ze wzrostem obciążeń cieplnych, tym większym, im wyższa jest temperatura czynnika roboczego. Wysokie temperatury wymusiły zastosowanie w turbinach systemów chłodzenia, których zadaniem jest niedopuszczenie do nadmiernego nagrzewania elementów maszyny. Rozpatrywane jest zagadnienie działania systemu chłodzenia podczas rozruchu. Wprowadzenie dodatkowego strumienia zmienia warunki wymiany ciepła na powierzchni chłodzonych elementów i prowadzi do uzyskania pola temperatury innego, niż w turbinie bez chłodzenia. W pracy przedstawiono wyniki badań umożliwiające ocenę stanu cieplnego i wytrzymałościowego głównych elementów turbiny.
Start-up of a steam turbine incurres in high thermal loads. Their level is proportional to the level of the live steam temperature. High level of the temperature demands application of cooling systems to protect the turbine against overheating. The problem under the analysis here is focused on the operation of the cooling system during start-up. The presence of an additional steam flow changes the conditions of heat transfer at the surfaces of the components and causes the temperature field different from the one found in the uncooled turbine. The paper presents the research that aims to evaluate the thermal and strength state of the main components of a supercritical steam turbine.
Źródło:: Archiwum Energetyki; 2013, 43, 1/2; 147-155
0066-684X
Pojawia się w:: Archiwum Energetyki
Dostawca treści:: Biblioteka Nauki

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