Experimental and CFD analysis on the pressure ratio and entropy increment in a cover-plate pre-swirl system of gas turbine engine

Liu, Gaowen; Gong, Wenbin; Wu, Heng; Lin, Aqiang

doi:10.1080/19942060.2021.1884600

Cited by 18 publications

(6 citation statements)

References 29 publications

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“…To further evaluate the use of ribs to reduce swirl velocity, an aeroengine preswirled cooling air delivery chamber was modeled incorporating a brush seal with a ribbed front plate in a modified outer seal position. The model geometry was based on an engine representative preswirl system (Chew et al, 2003;Liu G. et al, 2021;Liu Y. et al, 2021), with the introduction of an outer chamber, and is shown in Figure 18. To accommodate the selected design of ribs, circumferential periodicity was assumed for a 2.371 °sector.…”

Section: Preswirl Chamber Application Computational Modelmentioning

confidence: 99%

Flow Conditioning to Control the Effects of Inlet Swirl on Brush Seal Performance in Gas Turbine Engines

et al. 2022

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When subject to highly swirling inlet flow, the bristles on the upstream face of a brush seal in gas turbine engines tend to slip circumferentially, which may lead to aeromechanical instability and seal failure. In this article, a new design of the front plate of brush seal, which mitigates this effect, is presented. Angled ribs on the upstream side of the front plate are used to reduce the swirl of the flow impacting on the bristle pack. The effects of the rib geometry, including angle of inclination and height-to-spacing ratio, are investigated using computational fluid dynamics, and a bulk porous medium model of the bristle pack, on a simple seal geometry. Results show that the ribs can effectively regulate the flow upstream of the bristle pack, reducing the swirl and channeling flow radially inward to the sealing section, resulting in decreased circumferential forces on the bristles. Ribs inclined at 20° to the radial direction and with height-to-spacing ratio of 0.4 were selected as the most effective of those investigated for the seal geometry under study. A model of an aeroengine preswirled cooling air chamber was created to give insight into the inlet swirl boundary conditions that a preswirl seal brush seal could be subjected to at a range of leakage flow rates and inlet swirl velocities. The new design and upstream roughness feature substantially reduced inlet swirl velocity incident on the bristle pack. The findings in this work could have a significant impact on brush seal design and, in particular, mitigate a significant operational risk of swirl-induced instability in high-pressure, high-speed shaft seal locations.

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Section: Preswirl Chamber Application Computational Modelmentioning

confidence: 99%

Flow Conditioning to Control the Effects of Inlet Swirl on Brush Seal Performance in Gas Turbine Engines

et al. 2022

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“…Commonly, the pre-swirl nozzles generate significant temperature and pressure drops. Although flow and heat transfer have been extensively studied in the axial and cover-plate pre-swirl systems [5][6][7][8], the radial pre-swirl system has received less attention. Because of the compact layout and the requirement for high pressures, the airflow in the radial pre-swirl system is structured to flow from a low radius to a high radius.…”

Section: Introductionmentioning

confidence: 99%

Effect of Impellers on the Cooling Performance of a Radial Pre-Swirl System in Gas Turbine Engines

Shen,

Wang,

Liang

2024

Aerospace

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Impellers are utilized to increase pressure to ensure that a radial pre-swirl system can provide sufficient cooling airflow to the turbine blades. In the open literature, the pressurization mechanism of the impellers was investigated. However, the effect of impellers on the cooling performance of the radial pre-swirl system was not clear. To solve the aforementioned problem, tests were carried out to assess the temperature drop in a radial pre-swirl system with various impeller configurations (impeller lengths l/b ranging from 0 to 0.333). Furthermore, numerical simulations were used to investigate the flow and heat transfer characteristics of the radial pre-swirl system at high rotating Reynolds numbers. Theoretical and experimental investigations revealed that the pre-swirl jet and output power generate a significant temperature drop, but the impellers have no obvious effect on the system temperature drop. By increasing the swirl ratio, the impellers reduce the field synergy angle and thus improve convective heat transfer on the turbine disk. In addition, increasing the impeller length can reduce the volume-averaged field synergy angle and improve heat transfer, but the improvement effectiveness decreases as the impeller length increases. Thus, the study concluded that impellers could improve the cooling performance of the radial pre-swirl system by enhancing disk cooling.

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“…For gas turbines, the highpressure rotor and low-pressure rotor are coupled with each other, and the mechanical internal components are coupled in a cascade. For each rotor through the fluid interaction, there is a certain correlation [13,14]. Therefore, ICA is no longer applicable.…”

Section: Introductionmentioning

confidence: 99%

Convolutive blind source separation in the frequency domain of mechanical noise for gas turbines based on bounded component analysis

Cheng¹,

Chen²,

Song³

et al. 2022

Meas. Sci. Technol.

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Noise source identification of gas turbines can provide basis and guidance for vibration and noise reduction of gas turbines. Independent component analysis (ICA) which is one of the most popular techniques of blind source separation (BSS) widely used in vibration and noise sources of mechanical systems. However, ICA is suitable for independent source signals. In order to identify dependent mechanical noise sources of gas turbines, a convolutive blind source separation in frequency domain based on bounded component analysis (BCA) is proposed. First, the basic theory of BSS and BCA is introduced in detail. The convolutive mixing in time domain is transformed into an instantaneous mixing in frequency domain by STFT, and complex BCA is performed at each frequency bin. Then a permutation alignment method based on local and global optimization is proposed to solve the problem of the fuzziness of permutation. Finally, the accuracy and robustness of the proposed method are studied and compared through typical numerical studies and experimental studies on a three-rotor experimental bench. The results show that the proposed method can effectively separate and identify independent and dependent source signals.

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Experimental and CFD analysis on the pressure ratio and entropy increment in a cover-plate pre-swirl system of gas turbine engine

Cited by 18 publications

References 29 publications

Flow Conditioning to Control the Effects of Inlet Swirl on Brush Seal Performance in Gas Turbine Engines

Flow Conditioning to Control the Effects of Inlet Swirl on Brush Seal Performance in Gas Turbine Engines

Effect of Impellers on the Cooling Performance of a Radial Pre-Swirl System in Gas Turbine Engines

Convolutive blind source separation in the frequency domain of mechanical noise for gas turbines based on bounded component analysis

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