Design optimization of a compressor transition S-shaped duct using a teaching–learning-based optimization algorithm

Sharma, M.P.; Baloni, Beena D.

doi:10.1007/s40430-019-2072-5

Cited by 6 publications

(2 citation statements)

References 33 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…-Implementing non-axisymmetric end wall contouring on hub and shroud wall, a 19% length reduction of the baseline duct could be further possible along with a 2% reduction in loss. Sharma and Baloni [76] Teaching learning based optimization algorithm -The proposed design showed 28.80%, 36.67% reduction in pressure loss and non-uniformity respectively despite 14.74% length reduction.…”

Section: Authors Technique Remarkmentioning

confidence: 96%

Review on the aerodynamics of intermediate compressor duct

Sharma¹,

Baloni²

2020

JMES

Self Cite

View full text Add to dashboard Cite

In a turbofan engine, the air is brought from the low to the high-pressure compressor through an intermediate compressor duct. Weight and design space limitations impel to its design as an S-shaped. Despite it, the intermediate duct has to guide the flow carefully to the high-pressure compressor without disturbances and flow separations hence, flow analysis within the duct has been attractive to the researchers ever since its inception. Consequently, a number of researchers and experimentalists from the aerospace industry could not keep themselves away from this research. Further demand for increasing by-pass ratio will change the shape and weight of the duct that uplift encourages them to continue research in this field. Innumerable studies related to S-shaped duct have proven that its performance depends on many factors like curvature, upstream compressor’s vortices, swirl, insertion of struts, geometrical aspects, Mach number and many more. The application of flow control devices, wall shape optimization techniques, and integrated concepts lead a better system performance and shorten the duct length. This review paper is an endeavor to encapsulate all the above aspects and finally, it can be concluded that the intermediate duct is a key component to keep the overall weight and specific fuel consumption low. The shape and curvature of the duct significantly affect the pressure distortion. The wall static pressure distribution along the inner wall significantly higher than that of the outer wall. Duct pressure loss enhances with the aggressive design of duct, incursion of struts, thick inlet boundary layer and higher swirl at the inlet. Thus, one should focus on research areas for better aerodynamic effects of the above parameters which give duct design with optimum pressure loss and non-uniformity within the duct.

show abstract

Section: Authors Technique Remarkmentioning

confidence: 96%

Review on the aerodynamics of intermediate compressor duct

Sharma¹,

Baloni²

2020

JMES

Self Cite

View full text Add to dashboard Cite

show abstract

“…After optimizing the design, the radial drop length ratio of the transition duct had been increased by 11.6% compared with that of the prototype, the total pressure loss had been reduced by 36.9% and the parameter distribution at the outlet was more uniform. In 2019, Sharma et al 17 applied a multi-objective teaching–learning-based optimization algorithm to the s-shaped transition compressor duct. Compared with the prototype, the total pressure loss and non-uniformity of the optimized duct were reduced by 28.80% and 36.67%, respectively, despite the overall length being reduced by 14.74%.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation of an aggressive s-shaped compressor transition duct with boundary layer suction

Huang

Yang

Han

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

Aggressive s-shaped compressor transition ducts are important components in the connection between upstream boosters and downstream high-pressure compressors. The flow path is an s-shaped channel with struts and a large radial drop length ratio, which breaks through the limitations of traditional design and has a large aerodynamic loss. Therefore, this paper considers an aggressive s-shaped compressor transition duct in a geared turbofan engine and creatively proposes a method for controlling the flow separation through boundary layer suction. The results show that hub suction reduces the losses of the aggressive s-shape transition duct. As the mass flow rate of hub suction increases, the total pressure loss coefficient decreases and the rate of reduction in the total pressure loss slows down. Combined boundary layer suction reduces the total pressure loss to a greater extent. On the premise that the location of blade suction remains unchanged, the optimal location for the circumferential slot of hub suction is at 20% of the axial chord length of the strut, whereby the total pressure loss coefficient decreases by about 30% compared with the case of no suction. When the mass flow rate of suction is fixed at 3% of the inlet mass flow rate, a distribution of 0.5% from blade suction and 2.5% from hub suction reduces the total pressure loss by 1.6% compared with the case where all 3% comes from hub suction. The distribution of the mass flow rate for combined boundary layer suction has an optimal ratio.

show abstract