Effect of inverse blade angle slots on a transonic rotor performance and stability

Zhang, Haoguang; Liu, Wenhao; Wang, Enhao; Chu, Wuli; Ding, Kejin; Yan, Song

doi:10.1016/j.ast.2019.105596

Cited by 11 publications

(6 citation statements)

References 8 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Although there are some discrepancies in predicting the pressure ratio and efficiency characteristics, it is concluded from Figure 7 that the predicted flow field is highly similar to the experimental results. Furthermore, the application of the commercial CFD software NUMECA TM to predict the flow field of Rotor 67 with the Spalart-Allmaras turbulence model has been widely validated by many researchers [23][24][25]. Thus, the predicted results can be considered acceptable for the purposes of this paper.…”

Section: Numerical Methods and Validationmentioning

confidence: 97%

Implementation of Three-Dimensional Inverse Design and Its Application to Improve the Compressor Performance

et al. 2020

View full text Add to dashboard Cite

The implementation of a three-dimensional viscous inverse design used for an axial compressor is introduced in this paper. The derivation process of the inverse design algorithm is also described in detail. Moreover, an improved blade update method and a modified relaxation factor are included to enhance the inverse design algorithm. The inverse design is built on an in-house inverse design module coupled with commercial Computational Fluid Dynamic (CFD) software NUMECATM. In contrast to analysis design, the pressure loading and the normal thickness distribution along the blade surfaces are prescribed during the process of inverse design. The numerical methods used to solve the flow field are verified using the experimental data of the transonic fan rotor NASA Rotor 67. A recovery test for the Rotor 67 is carried out to validate the developed three-dimensional inverse design tool. To explore the potential application of the inverse design system, it is then used to improve the aerodynamic performance of a transonic fan Rotor 67 and a multi-row compressor Stage 35 at a near peak efficiency point by reorganizing the pressure loading distribution on the blade surfaces.

show abstract

Section: Numerical Methods and Validationmentioning

confidence: 97%

Implementation of Three-Dimensional Inverse Design and Its Application to Improve the Compressor Performance

et al. 2020

View full text Add to dashboard Cite

show abstract

“…Accurate and reliable predictions of airloads and structural loads in maneuver are challenging because of the highly nonlinear and transient nature of the flight. Among others, three-dimensional transonic effects [5] near the blade tip in the advancing side, reversed flow [6] and dynamic stall (DS) [7] in the retreating side, and blade-vortex interaction (BVI) events [8] in the rear portions of the rotor disk are the major factors of the aeromechanics analysis that should be countered correctly. Highly unsteady air flows and large blade deformations make the analysis more involved and demand the most sophisticated solution technologies such as CFD/CSD coupling to correctly identify the complex phenomena and understand the detailed physics related with the aeroelastic behavior of the vehicle in motion.…”

Section: Introductionmentioning

confidence: 99%

Air and Structural Loads Analysis of a 5-Ton Class Rotorcraft in a Pull-Up Maneuver Using CFD/CSD Coupled Approach

Hong,

Kim,

Park

et al. 2024

Aerospace

View full text Add to dashboard Cite

The air and structural loads of a 5-ton class light helicopter (LH) rotor in a 2.24 g pull-up maneuver are investigated using a coupling between the computational structural dynamics (CSD) and computational fluid dynamics (CFD) methods. The LH rotor is characterized by a five-bladed system with elastomeric bearings and inter-bladed dampers. The periodic trim solution along with the converged CFD/CSD delta airloads obtained in steady-level flight (advance ratio of 0.287) are used to perform the transient CSD maneuver analysis. The resulting vehicle attitude angles and velocity profiles of the aircraft are then prescribed in the quasi-static (QS) CFD maneuver analysis. It is demonstrated that the present QS approach provides an effective means for the maneuver loads’ analysis. The important flow behaviors such as BVI (blade–vortex interaction)-induced oscillations and the negative pitching moment peaks met in maneuver flight are captured nicely with the proposed method. Either the vortex trajectories or the surface pressure distributions are examined to identify the sources of the oscillations. A loose CFD/CSD coupling (LC) is used to predict the blade elastic motions, structural moments, and pitch link loads at the specified maneuver revolution of the rotor and also to correlate these with the transient CSD-based predictions. A reasonable correlation is obtained. The LC results show more pronounced 5P (five per revolution) oscillations on the structural response than those of the CSD-based methods.

show abstract

“…With 6 slots per passage covering one-third of the rotor's axial chord, the treatment increased the stall margin by about 22% with a slight increase in isentropic efficiency. Zhang et al [5] tested an inverse blade angle slots design on the NASA Rotor 67 and achieved the highest stall margin improvement of 24.3%, accompanied by a 0.755% loss in efficiency.…”

Section: Introductionmentioning

confidence: 99%

Casing treatment using oblique slots for a single-stage transonic axial compressor

Vuong

Kim

2022

J. Phys.: Conf. Ser.

View full text Add to dashboard Cite

This work presents a casing treatment design using oblique slots to improve the stability of a single-stage transonic axial compressor, NASA Stage 37. 36 individual slots are distributed uniformly on the rotors’ shroud. Numerical simulations were performed to find the effects of the casing treatment on the compressor’s stability as well as the adiabatic efficiency and pressure ratio. The oblique slots were found to effectively alleviate the negative influence of the tip leakage flow on the compressor’s performance, thus increasing the stall margin without significant sacrifices in efficiency and pressure rise. Three geometric parameters of the casing treatment were examined. The results showed that, with the oblique slots, the highest stall margin reached 13.59% - a 37% increase from the smooth casing case, with about 0.17% and 0.09% reductions in the peak efficiency and maximum pressure ratio, respectively.

show abstract

Effect of inverse blade angle slots on a transonic rotor performance and stability

Cited by 11 publications

References 8 publications

Implementation of Three-Dimensional Inverse Design and Its Application to Improve the Compressor Performance

Implementation of Three-Dimensional Inverse Design and Its Application to Improve the Compressor Performance

Air and Structural Loads Analysis of a 5-Ton Class Rotorcraft in a Pull-Up Maneuver Using CFD/CSD Coupled Approach

Casing treatment using oblique slots for a single-stage transonic axial compressor

Contact Info

Product

Resources

About