Effect of nozzle box arrangement on the aerodynamic performance of a single stage partial admission turbine

Pan, Yang; Yuan, Qi; Niu, Guangshuo; Gu, Jianwen Wendy; Zhu, Guangyu

doi:10.1016/j.applthermaleng.2019.113911

Cited by 14 publications

(5 citation statements)

References 9 publications

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“…(1) Non-uniform intake imposes bending and radial moments on the rotor, which may result in rotor vibrations [6][7][8] and even faults [9], thus affecting bearing safety [10]; (2) Non-uniform intake causes mixed loss in the cascade channel [11][12][13][14] or blast loss [15,16], and a mismatch between the chamber outlet airflow angle and the geometric angle of the first stage static cascade causes shock loss [17]; (3) Non-uniform intake causes an increase in the amplitude of airflow excitation forces on the first-stage dynamic and static lobes [18] and complex excitation force frequencies [5,13,[19][20][21][22].…”

Section: Figurementioning

confidence: 99%

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Research on the Aerodynamic Performance and Collaborative Optimization Design of the Full-Scale Compact Inlet Chamber of a Nuclear-Powered Steam Turbine

Zhang,

Jiang,

Xie

et al. 2024

Machines

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In nuclear-powered steam turbines, the aerodynamic performance of the inlet chamber tends to be contradictory to the compact design, which makes it difficult to achieve optimal efficiency and power in a nuclear-powered steam turbine. In this study, the quantitative correlation between compact design and aerodynamic performance was investigated to reveal the interaction mechanism between the aerodynamic performance of the inlet chamber of the steam turbine with its compactness. First, the effects of peripheral quantity and arrangement of inlets in the chamber inlet on its aerodynamic performance were studied. The results indicated that the proposed cross configuration exhibited optimized aerodynamic performance in multiple aspects. Then, the effects of two compactness indices (inlet/outlet area ratio and axial spacing at outlet) on the aerodynamic performance of the inlet chamber were investigated. The results indicated that the volume of the inlet chamber was proportional to the inlet/outlet area ratio, and an appropriate design of the inlet chamber can achieve compactness without significantly affecting its aerodynamic performance. In addition, the influencing mechanism of the compact optimization design on the aerodynamic performances of the inlet chamber was revealed. This study provides references for optimization designing an effective and compacted inlet chamber of steam turbines.

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Section: Figurementioning

confidence: 99%

Section: Figurementioning

confidence: 99%

Research on the Aerodynamic Performance and Collaborative Optimization Design of the Full-Scale Compact Inlet Chamber of a Nuclear-Powered Steam Turbine

Zhang,

Jiang,

Xie

et al. 2024

Machines

View full text Add to dashboard Cite

show abstract

“…For each segment, six stacks are considered that three of them are in the upper part and three in the lower part of the compressor allowing air mass flow rate to be allocated evenly around turbine circumference (Figure 11). This configuration helps to avoid partial admission turbine and its related losses, particularly in supersonic/ transonic axial turbines by influencing destructive vibrations 28 and reducing aerodynamic performance 29 particularly for supersonic entrance. 30 As a result, the formula used in Ref.…”

Section: Compressormentioning

confidence: 99%

A novel hybrid aircraft propulsion based on the DEA compressor—Part A: Design

Aryana¹

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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This two-part article introduces a novel hybrid propulsion system based on the DEA compressor. The system encompasses a Pulse Detonation TurboDEA as the master engine that supplies several full-electric ancillary thrusters called DEAThruster. The system, called the propulsion set, can be categorized as a distributed propulsion system based on the design mission and number of ancillary thrusters. Part A of this article explains the design process comprising intake, compressor, detonation process, diffuser, axial turbine, and the exit nozzle. The main target is to design a high-performance low emission propulsion system capable of serving in a wide range of altitudes and flight Mach numbers that covers altitudes up to 20,000 m and flight Mach number up to the hypersonic edge. Designing the propulsion set, the design point is considered at the static condition in the sea level. Design results show the propulsion set can satisfy all requirements necessary for its mission.

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“…Researchers generally concurred that, in terms of flow channel structure, reducing the axial clearance between the nozzle and rotor within a suitable range can result in greater efficiency [12,13] and with decreasing mass flow rate, the efficiency and optimum speed ratio decline. Researchers generally concurred with the effect of the number of inlet nozzles that an increase in the number of inlet nozzles with the same partial admission degree will duplicate the admission losses and hence decrease turbine efficiency [14,15]. Researchers have proposed that partial admission losses rise with increasing inlet arc spacing for the effect of inlet nozzle position [16,17].…”

Section: Introductionmentioning

confidence: 98%

“…Researchers have proposed that partial admission losses rise with increasing inlet arc spacing for the effect of inlet nozzle position [16,17]. The impacts of blade solidity [18,19], aspect ratio [20,21], and nozzle outlet airflow angle [22,23] on partial admission turbine performance have been the main areas of research for blade parameters. Currently, the nozzle outlet airflow angle is typically controlled by altering the orientation of the nozzle alignment, but there hasn't been much investigation into controlling the airflow direction by altering the stator installation angle (SIA).…”

Section: Introductionmentioning

confidence: 99%

Compressed air energy storage system: Effect of variable relative stator installation angle on nozzle governing turbine performance

Guan,

Li,

Zhu

et al. 2024

J. Phys.: Conf. Ser.

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The air storage pressure of compressed air energy storage system gradually decreases during the process of energy release, and a reasonable air distribution method for the turbine is required to make the turbine work efficiently in this process. In this paper, based on the single nozzle governing method, the effect of the variation of the full circumferential relative stator installation angle on the system performance improvement under the rated output work condition is investigated. It is shown that the specific work of the variable relative stator installation angle can be improved by up to 6.3 % relative to the design stator installation angle and up to 15.7 % relative to the throttle governing method under the base pressure of 10.0 MPa. With the same absence of throttling losses, the specific work of 3-nozzle inlets method is higher than that of 4-nozzle inlets method, and the turbine internal losses are reduced by 10.6 %. This study provides a theoretical basis for the design, optimization and operation control of nozzle governing turbines.

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Effect of nozzle box arrangement on the aerodynamic performance of a single stage partial admission turbine

Cited by 14 publications

References 9 publications

Research on the Aerodynamic Performance and Collaborative Optimization Design of the Full-Scale Compact Inlet Chamber of a Nuclear-Powered Steam Turbine

Research on the Aerodynamic Performance and Collaborative Optimization Design of the Full-Scale Compact Inlet Chamber of a Nuclear-Powered Steam Turbine

A novel hybrid aircraft propulsion based on the DEA compressor—Part A: Design

Compressed air energy storage system: Effect of variable relative stator installation angle on nozzle governing turbine performance

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