Effect of Endwall Contouring on a Transonic Turbine Blade Passage: Part 1—Aerodynamic Performance

Abraham, Santosh; Panchal, Kapil; Ekkad, Srinath V.; Ng, Wing; Lohaus, Andrew S.; Malandra, Anthony

doi:10.1115/gt2012-68425

Cited by 6 publications

(9 citation statements)

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“…The present study is an extension of the work presented by Abraham et al [21] and Blot et al [22] to incorporate effects of an upstream purge slot and mateface gap on the same linear cascade set-up. The measurements were carried out for a diverging planar endwall (P) as well as two contoured endwalls which shall be henceforth referred to as Aero…”

Section: Secondary Flow Physicsmentioning

confidence: 87%

“…However, the location was chosen since it yields a better estimate of reduction of losses due to endwall contouring, as reported by Abraham et al [21] where they saw a 3% reduction based on the measurements at 0.1 Cax which magnified to 17% at 1.0 Cax. While the contours, may not be very reliable indicators in pinpointing specific flow features on the endwall, the results can offer insight with regards to a general trend with respect to the relative impact with geometry variation and cooling features.…”

Section: Contour (A) and Opt1 (O)mentioning

confidence: 99%

“…The aerodynamic performance at transonic speeds for a linear cascade with a diverging endwall at design and off design conditions was published by Abraham et al [21]. In their work, they measured the loss coefficients at both 0.1-Cax and 1.0-Cax from the trailing edge of an airfoil.…”

Section: Secondary Flow Physicsmentioning

confidence: 99%

“…Aero Contour has been tested previously by Abraham et al [21] and Blot et al [22]. A new contour design geometry was also tested this year, which is being referred to here as the OPT1 endwall.…”

Section: Contour (A) and Opt1 (O)mentioning

confidence: 99%

“…Since the study is a continuation from the works of Abraham et al [21]. and Blot et al [22], an identical test section cascade geometry is used.…”

Section: Cascade Setupmentioning

confidence: 99%

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Aerodynamic Performance of a Transonic Turbine Blade Passage in Presence of Upstream Slot and Mateface Gap With Endwall Contouring

Jain

Roy

et al. 2014

Volume 2C: Turbomachinery

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The present study investigates mixed out aerodynamic loss coefficient measurements for a high turning, contoured endwall passage under transonic operating conditions in presence of upstream purge slot and mateface gap. The upstream purge slot represents the gap between stator-rotor interface and the mateface gap simulates the assembly feature between adjacent airfoils in an actual high pressure turbine stage. While the performance of the mateface and upstream slot has been studied for lower Mach number, no studies exist in literature for transonic flow conditions. Experiments were performed at the Virginia Tech's linear, transonic blow down cascade facility. Measurements were carried out at design conditions (isentropic exit Mach number of 0.87, design incidence) without and with coolant blowing. Upstream leakage flow of 1.0% coolant to mainstream mass flow ratio (MFR) was considered with the presence of mateface gap. There was no coolant blowing through the mateface gap itself. Cascade exit pressure measurements were carried out using a 5-hole probe traverse at a plane 1.0Cax downstream of the trailing edge for a planar geometry and two contoured endwalls. Spanwise measurements were performed to complete the entire 2D loss plane from endwall to midspan, which were used to plot pitchwise averaged losses for different span locations and loss contours for the passage. Results reveal significant reduction in aerodynamic losses using the contoured endwalls due to the modification of flow physics compared to a non contoured planar endwall.iii

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Section: Secondary Flow Physicsmentioning

confidence: 87%

Section: Contour (A) and Opt1 (O)mentioning

confidence: 99%

Section: Secondary Flow Physicsmentioning

confidence: 99%

Section: Contour (A) and Opt1 (O)mentioning

confidence: 99%

“…Since the study is a continuation from the works of Abraham et al [21]. and Blot et al [22], an identical test section cascade geometry is used.…”

Section: Cascade Setupmentioning

confidence: 99%

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Aerodynamic Performance of a Transonic Turbine Blade Passage in Presence of Upstream Slot and Mateface Gap With Endwall Contouring

Jain

Roy

et al. 2014

Volume 2C: Turbomachinery

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Effect of Endwall Contouring on a Transonic Turbine Blade Passage: Heat Transfer Performance

Panchal¹,

Abraham

Roy

et al. 2016

Journal of Turbomachinery

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Effect of turbine endwall contouring on its aerodynamic performance has been widely studied, but only a few studies are available in the open literature investigating its effect on heat transfer performance; especially at transonic exit Mach number conditions. In this paper, we report a study of effect of contouring on endwall heat transfer performance of a high-turning high-pressure (HP) turbine blade passage operating under transonic exit conditions. The paper describes comparison of heat transfer performance of two contoured endwall geometries, one aerodynamically optimized (AO) and the other heat transfer optimized (HTO), with a baseline, noncontoured geometry. The endwall geometries were experimentally investigated at Virginia Tech's transient, blow down, transonic linear cascade facility at three exit Mach numbers, Mex= 0.71, 0.88(design) and 0.95, for their heat transfer performance. Endwall surface temperatures were measured using infrared (IR) thermography and local heat transfer coefficient (HTC) values were calculated using measured temperatures. A camera matrix model-based data postprocessing technique was developed to relate the two-dimensional images captured by IR camera to three-dimensional endwall contours. The measurement technique and the methodology for postprocessing of the heat transfer coefficient data have been presented in detail. Discussion and interpretation of experimental results have been augmented using aerodynamic CFD simulations of the geometries. Both the contoured endwalls demonstrated a significant reduction in the overall average heat transfer coefficient values of the order of 10%. The surface Stanton number distributions also indicated a reduction in the level of hot spots for most of the endwall surface. However, at some locations an increase was also observed, especially in the area near the leading edge (LE). The results indicate that the endwall contouring could significantly improve heat transfer performance of turbine passages.

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Aerodynamic Loss for a Turbine Blade With Endwall Leakage Features and Contouring

Lynch

Thole

Kohli

et al. 2013

Volume 6A: Turbomachinery

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Secondary flows near the endwall of a turbine blade contribute to a loss in aerodynamic performance in the engine. Further reductions in performance occur when the secondary flows interact with leakage flow from necessary clearance features, such as the clearance gap between the blade rotor and an upstream stator or gaps between adjacent blade platforms. Non-axisymmetric endwall contouring has been shown to reduce the strength of secondary flows near the endwall, but relatively little research has been done to test the sensitivity of the contouring to the endwall leakage features. This paper describes aerodynamic measurements taken downstream of a cascade with representative leakage features. In general, upstream leakage flow with swirl relative to the blade increased aerodynamic loss, relative to leakage that was matched to the blade wheelspeed. Non-axisymmetric contouring for an endwall without a platform gap reduced underturning of the flow but had no effect on overall loss, relative to a flat endwall without a gap. A contoured endwall with a platform gap had 12% higher mixed-out loss than a contoured endwall without a gap.

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Effect of Endwall Contouring on a Transonic Turbine Blade Passage: Part 1—Aerodynamic Performance

Cited by 6 publications

References 0 publications

Aerodynamic Performance of a Transonic Turbine Blade Passage in Presence of Upstream Slot and Mateface Gap With Endwall Contouring

Aerodynamic Performance of a Transonic Turbine Blade Passage in Presence of Upstream Slot and Mateface Gap With Endwall Contouring

Effect of Endwall Contouring on a Transonic Turbine Blade Passage: Heat Transfer Performance

Aerodynamic Loss for a Turbine Blade With Endwall Leakage Features and Contouring

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