Influence of Blade Fracture on the Flow of Rotor-Stator Systems with Centrifugal Superposed Flow
Rotor-stator cavities are often found in turbomachinery; they supply cold air that is bled from the compressor to the turbine blades. The pressure of the outlet of a rotor-stator cavity is axisymmetric under normal circumstances. However, its pressure would be non-axisymmetric in the event of blade...
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| Format: | Article |
| Language: | English |
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MDPI AG
2022-02-01
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| Series: | Aerospace |
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| Online Access: | https://www.mdpi.com/2226-4310/9/2/106 |
| _version_ | 1797483877159141376 |
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| author | Gang Zhao Tian Qiu Peng Liu |
| author_facet | Gang Zhao Tian Qiu Peng Liu |
| author_sort | Gang Zhao |
| collection | DOAJ |
| description | Rotor-stator cavities are often found in turbomachinery; they supply cold air that is bled from the compressor to the turbine blades. The pressure of the outlet of a rotor-stator cavity is axisymmetric under normal circumstances. However, its pressure would be non-axisymmetric in the event of blade fracture. The impact of blade fracture on a rotor-stator cavity with centrifugal superposed flow is studied in this paper. The Euler number <i>E</i>, the rotational Reynolds number <inline-formula><math display="inline" xmlns="http://www.w3.org/1998/Math/MathML"><semantics><mrow><mi>R</mi><msub><mi>e</mi><mi>φ</mi></msub></mrow></semantics></math></inline-formula>, and the low-pressure zone range <i>θ</i> are investigated and, for the first time, with the non-axisymmetrical boundary conditions employing numerical simulation. The results of the numerical calculations show that after turbine blade fracture, the velocity is more affected in the downstream region at a high radius, especially when the <inline-formula><math display="inline" xmlns="http://www.w3.org/1998/Math/MathML"><semantics><mrow><mi>R</mi><msub><mi>e</mi><mi>φ</mi></msub></mrow></semantics></math></inline-formula> is large. As for the distribution of the mass flow rate, there may be a critical <inline-formula><math display="inline" xmlns="http://www.w3.org/1998/Math/MathML"><semantics><mrow><msub><mi>θ</mi><mi>c</mi></msub></mrow></semantics></math></inline-formula> at which the other blades are least affected. The <inline-formula><math display="inline" xmlns="http://www.w3.org/1998/Math/MathML"><semantics><mrow><msub><mi>θ</mi><mi>c</mi></msub></mrow></semantics></math></inline-formula> would increase as the <inline-formula><math display="inline" xmlns="http://www.w3.org/1998/Math/MathML"><semantics><mrow><mi>R</mi><msub><mi>e</mi><mi>φ</mi></msub></mrow></semantics></math></inline-formula> or the <i>E</i> increase, and the <inline-formula><math display="inline" xmlns="http://www.w3.org/1998/Math/MathML"><semantics><mrow><msub><mi>θ</mi><mi>c</mi></msub><mo>≅</mo><mn>0.2</mn></mrow></semantics></math></inline-formula> when <inline-formula><math display="inline" xmlns="http://www.w3.org/1998/Math/MathML"><semantics><mrow><msub><mi>C</mi><mi>w</mi></msub><mo>=</mo><mn>10</mn><mo>,</mo><mn>137</mn></mrow></semantics></math></inline-formula>, <inline-formula><math display="inline" xmlns="http://www.w3.org/1998/Math/MathML"><semantics><mrow><mi>R</mi><msub><mi>e</mi><mi>φ</mi></msub><mo>=</mo><mn>5.12</mn><mo>×</mo><msup><mrow><mn>10</mn></mrow><mn>5</mn></msup></mrow></semantics></math></inline-formula>, and <inline-formula><math display="inline" xmlns="http://www.w3.org/1998/Math/MathML"><semantics><mrow><mn>0.2</mn><mo>≤</mo><mi>E</mi><mo>≤</mo><mn>0.4</mn></mrow></semantics></math></inline-formula>. In addition, the thrust coefficient increases as the <i>E</i> or the <inline-formula><math display="inline" xmlns="http://www.w3.org/1998/Math/MathML"><semantics><mi>θ</mi></semantics></math></inline-formula> increases, and the increase in the thrust coefficient does not exceed 4% when the <inline-formula><math display="inline" xmlns="http://www.w3.org/1998/Math/MathML"><semantics><mrow><mi>E</mi><mo>=</mo><mn>0.2</mn><mo> </mo><mrow><mi>and</mi><mo> </mo><mi>the</mi></mrow><mo> </mo><mi>θ</mi><mo>=</mo><mn>0.1</mn></mrow></semantics></math></inline-formula> in this paper. However, the moment coefficient on the rotating shaft is almost independent of the <i>E</i> and the <i>θ</i>. An increase in the <inline-formula><math display="inline" xmlns="http://www.w3.org/1998/Math/MathML"><semantics><mrow><mi>R</mi><msub><mi>e</mi><mi>φ</mi></msub></mrow></semantics></math></inline-formula> will reduce the effect of turbine blade fracture on the thrust and moment coefficients, when the <inline-formula><math display="inline" xmlns="http://www.w3.org/1998/Math/MathML"><semantics><mrow><mi>R</mi><msub><mi>e</mi><mi>φ</mi></msub></mrow></semantics></math></inline-formula> is small. |
| first_indexed | 2024-03-09T22:54:22Z |
| format | Article |
| id | doaj.art-9898e95f1537457d933e8f69f54e86e5 |
| institution | Directory Open Access Journal |
| issn | 2226-4310 |
| language | English |
| last_indexed | 2024-03-09T22:54:22Z |
| publishDate | 2022-02-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Aerospace |
| spelling | doaj.art-9898e95f1537457d933e8f69f54e86e52023-11-23T18:14:48ZengMDPI AGAerospace2226-43102022-02-019210610.3390/aerospace9020106Influence of Blade Fracture on the Flow of Rotor-Stator Systems with Centrifugal Superposed FlowGang Zhao0Tian Qiu1Peng Liu2School of Energy and Power Engineering, Beihang University, Xueyuan Road No. 37, Haidian District, Beijing 100191, ChinaResearch Institute of Aero-Engine, Beihang University, Xueyuan Road No. 37, Haidian District, Beijing 100191, ChinaResearch Institute of Aero-Engine, Beihang University, Xueyuan Road No. 37, Haidian District, Beijing 100191, ChinaRotor-stator cavities are often found in turbomachinery; they supply cold air that is bled from the compressor to the turbine blades. The pressure of the outlet of a rotor-stator cavity is axisymmetric under normal circumstances. However, its pressure would be non-axisymmetric in the event of blade fracture. The impact of blade fracture on a rotor-stator cavity with centrifugal superposed flow is studied in this paper. The Euler number <i>E</i>, the rotational Reynolds number <inline-formula><math display="inline" xmlns="http://www.w3.org/1998/Math/MathML"><semantics><mrow><mi>R</mi><msub><mi>e</mi><mi>φ</mi></msub></mrow></semantics></math></inline-formula>, and the low-pressure zone range <i>θ</i> are investigated and, for the first time, with the non-axisymmetrical boundary conditions employing numerical simulation. The results of the numerical calculations show that after turbine blade fracture, the velocity is more affected in the downstream region at a high radius, especially when the <inline-formula><math display="inline" xmlns="http://www.w3.org/1998/Math/MathML"><semantics><mrow><mi>R</mi><msub><mi>e</mi><mi>φ</mi></msub></mrow></semantics></math></inline-formula> is large. As for the distribution of the mass flow rate, there may be a critical <inline-formula><math display="inline" xmlns="http://www.w3.org/1998/Math/MathML"><semantics><mrow><msub><mi>θ</mi><mi>c</mi></msub></mrow></semantics></math></inline-formula> at which the other blades are least affected. The <inline-formula><math display="inline" xmlns="http://www.w3.org/1998/Math/MathML"><semantics><mrow><msub><mi>θ</mi><mi>c</mi></msub></mrow></semantics></math></inline-formula> would increase as the <inline-formula><math display="inline" xmlns="http://www.w3.org/1998/Math/MathML"><semantics><mrow><mi>R</mi><msub><mi>e</mi><mi>φ</mi></msub></mrow></semantics></math></inline-formula> or the <i>E</i> increase, and the <inline-formula><math display="inline" xmlns="http://www.w3.org/1998/Math/MathML"><semantics><mrow><msub><mi>θ</mi><mi>c</mi></msub><mo>≅</mo><mn>0.2</mn></mrow></semantics></math></inline-formula> when <inline-formula><math display="inline" xmlns="http://www.w3.org/1998/Math/MathML"><semantics><mrow><msub><mi>C</mi><mi>w</mi></msub><mo>=</mo><mn>10</mn><mo>,</mo><mn>137</mn></mrow></semantics></math></inline-formula>, <inline-formula><math display="inline" xmlns="http://www.w3.org/1998/Math/MathML"><semantics><mrow><mi>R</mi><msub><mi>e</mi><mi>φ</mi></msub><mo>=</mo><mn>5.12</mn><mo>×</mo><msup><mrow><mn>10</mn></mrow><mn>5</mn></msup></mrow></semantics></math></inline-formula>, and <inline-formula><math display="inline" xmlns="http://www.w3.org/1998/Math/MathML"><semantics><mrow><mn>0.2</mn><mo>≤</mo><mi>E</mi><mo>≤</mo><mn>0.4</mn></mrow></semantics></math></inline-formula>. In addition, the thrust coefficient increases as the <i>E</i> or the <inline-formula><math display="inline" xmlns="http://www.w3.org/1998/Math/MathML"><semantics><mi>θ</mi></semantics></math></inline-formula> increases, and the increase in the thrust coefficient does not exceed 4% when the <inline-formula><math display="inline" xmlns="http://www.w3.org/1998/Math/MathML"><semantics><mrow><mi>E</mi><mo>=</mo><mn>0.2</mn><mo> </mo><mrow><mi>and</mi><mo> </mo><mi>the</mi></mrow><mo> </mo><mi>θ</mi><mo>=</mo><mn>0.1</mn></mrow></semantics></math></inline-formula> in this paper. However, the moment coefficient on the rotating shaft is almost independent of the <i>E</i> and the <i>θ</i>. An increase in the <inline-formula><math display="inline" xmlns="http://www.w3.org/1998/Math/MathML"><semantics><mrow><mi>R</mi><msub><mi>e</mi><mi>φ</mi></msub></mrow></semantics></math></inline-formula> will reduce the effect of turbine blade fracture on the thrust and moment coefficients, when the <inline-formula><math display="inline" xmlns="http://www.w3.org/1998/Math/MathML"><semantics><mrow><mi>R</mi><msub><mi>e</mi><mi>φ</mi></msub></mrow></semantics></math></inline-formula> is small.https://www.mdpi.com/2226-4310/9/2/106rotor-stator systemnon-axisymmetric boundary conditionsnumerical simulationturbine blade fracture |
| spellingShingle | Gang Zhao Tian Qiu Peng Liu Influence of Blade Fracture on the Flow of Rotor-Stator Systems with Centrifugal Superposed Flow Aerospace rotor-stator system non-axisymmetric boundary conditions numerical simulation turbine blade fracture |
| title | Influence of Blade Fracture on the Flow of Rotor-Stator Systems with Centrifugal Superposed Flow |
| title_full | Influence of Blade Fracture on the Flow of Rotor-Stator Systems with Centrifugal Superposed Flow |
| title_fullStr | Influence of Blade Fracture on the Flow of Rotor-Stator Systems with Centrifugal Superposed Flow |
| title_full_unstemmed | Influence of Blade Fracture on the Flow of Rotor-Stator Systems with Centrifugal Superposed Flow |
| title_short | Influence of Blade Fracture on the Flow of Rotor-Stator Systems with Centrifugal Superposed Flow |
| title_sort | influence of blade fracture on the flow of rotor stator systems with centrifugal superposed flow |
| topic | rotor-stator system non-axisymmetric boundary conditions numerical simulation turbine blade fracture |
| url | https://www.mdpi.com/2226-4310/9/2/106 |
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