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Computational Investigations of Varying Solidity LP Turbine Cascade with Gurney Flap for Low Reynolds Numbers

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Proceedings of the National Aerospace Propulsion Conference

Part of the book series: Lecture Notes in Mechanical Engineering ((LNME))

Abstract

This paper reports computational investigation carried out on T106 LP turbine linear cascade to optimize the blade performance and reduce the blade count around the LP turbine rotor by decreasing blade solidity. T106 LP turbine blade of chord 196 mm and two different blade solidities of 1.25 and 1.176 were used. Passive flow control device—Gurney flap (GF) was attached to the trailing edge of the blade. The GFs of heights 1.33% Ch and 2% Ch were used in simulations. A two-equation eddy viscosity turbulence model, shear stress transport (SST) model was considered for all the computations along with gamma–theta (γ–θ) transition model. Computations were carried out for all the cases at four different Reynolds numbers. Lift coefficient, total pressure loss coefficient, overall integrated loss coefficient, and lift coefficient to overall integrated loss coefficient ratio were used as a measure of aerodynamic performance for the cascade. From the computations, it was found that on increasing the blade spacing by keeping the GF height constant, the performance of the turbine cascade decreases. But, the performance can be improved by increasing the flap height appropriately. For the cascade configuration with increased spacing, an optimal GF height was determined.

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Abbreviations

C:

Flow velocity

CD:

Drag coefficient

CD = 2*(S/Ch)*cos(α m)[(P01–P02)/C 2m ]

Ch:

Chord (mm)

Chx:

Axial chord (mm)

CL:

Lift coefficient

CL = 2*(S/Ch)*cos(α m)*[tan(α 1) + tan(α 2)] + CD*tan(α m)

CP:

Static pressure coefficient on blade surfaces

CP = (P01–P)/(P01–P1)

H:

Gurney flap height as a percentage of chord H = h/Ch*100(%)

h:

Gurney flap length (mm)

P:

Pressure

Re:

Reynolds number (ρ.C.Ch/μ)

S:

Cascade spacing (mm)

X:

Non-dimensional axial distance (x/Chx)

x:

Axial distance from leading edge (mm)

Y:

Non-dimensional pitch wise distance (y/Chx)

y:

Pitch-wise distance from leading edge (mm)

α:

Absolute flow angle

αm:

αm = atan[(tan(α1) + tan(α 2))/2]

ρ:

Density (kg/m3)

μ:

Dynamic viscosity (Pa.s)

ψ:

Total pressure loss coefficient

ψ = [P01-P02]/(0.5*ρ*C 22 )

ψint:

Overall integrated loss coefficient

ψint = (∫ψ*C2x)/(∫C2x)

0:

Stagnation conditions

1, 2:

Cascade inlet and outlet respectively

∞:

Free stream conditions

References

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Author information

Authors and Affiliations

  1. Department of Mechanical Engineering, R. V. College of Engineering, Bengaluru, Karnataka, India

    G. S. Srivatsa & Gajanan Tatpatti

Authors
  1. G. S. Srivatsa
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  2. Gajanan Tatpatti
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Corresponding authors

Correspondence to G. S. Srivatsa or Gajanan Tatpatti .

Editor information

Editors and Affiliations

  1. Indian Institute of Technology Kharagpur, Kharagpur, West Bengal, India

    Chetan S. Mistry

  2. Gas Turbine Research Establishment, Bangalore, Karnataka, India

    S. Kishore Kumar

  3. Indian Institute of Science Bangalore, Bangalore, Karnataka, India

    B. N. Raghunandan

  4. Gas Turbine Research Establishment, Bangalore, Karnataka, India

    Gullapalli Sivaramakrishna

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Srivatsa, G.S., Tatpatti, G. (2021). Computational Investigations of Varying Solidity LP Turbine Cascade with Gurney Flap for Low Reynolds Numbers. In: Mistry, C., Kumar, S., Raghunandan, B., Sivaramakrishna, G. (eds) Proceedings of the National Aerospace Propulsion Conference . Lecture Notes in Mechanical Engineering. Springer, Singapore. https://doi.org/10.1007/978-981-15-5039-3_6

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  • DOI: https://doi.org/10.1007/978-981-15-5039-3_6

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  • Publisher Name: Springer, Singapore

  • Print ISBN: 978-981-15-5038-6

  • Online ISBN: 978-981-15-5039-3

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