Aerodynamic Design and Performance of Five-Stage Transonic Axial-Flow Compressor

Kovach, Karl; Sandercock, D. M.

doi:10.1115/1.3673192

Cited by 6 publications

(8 citation statements)

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“…The tip clearance was modelled in two ways: firstly as a large clearance (3.3 % of span), two mesh cells high, and secondly as a more realistic clearance (1 % of span), six mesh cells high. Unfortunately Kovach and Sandercock, (1961) did not report the experimental running clearance, but a typical practical value on a primitive compressor would have been 1 % of span, as found by Von Backstrom (1987) on a similar compressor.…”

Section: Btob3d With Tip Clearancementioning

confidence: 97%

“…The first stage rotor of the pioneering NACA 5-stage transonic compressor (Kovach and Sandercock, 1961) was chosen as subject of this investigation for the following reasons: -its simple geometry (cylindrical casing, double circular arc blades, no inlet guide vanes), -the availability of experimental data, including losses, -the high first stage blade loading caused by the combination of high stage pressure ratio (1.4), low tip speed (335 m/s) and low tip solidity (1.0), -the highly cambered (11.7°) DCA blade tip sections operating under the above conditions, -the author's interest in selecting a code to model the first stage of a small compressor based on the NACA 5-stage design (Von Backstrom, 1987),…”

Section: The Compressormentioning

confidence: 99%

“…The blade row experimental data of Kovach and Sandercock (1961) consisted fundamentally of spanwise distributions of flow angle, total temperature and total and static pressure, all obtained by means of stationary probes. They checked the accuracy and consistency of their data by considering the following: mass flow balance; comparison of momentum to temperature rise efficiencies; and comparison of stator outlet to rotor outlet total temperatures.…”

Section: Experimental Datamentioning

confidence: 99%

“…Standard sea level conditions (288.2 K and 101.3 kPa) were assumed at the inlet. Hub and casing outlet static pressure were calculated from the design data of Kovach and Sandercock (1961). The inlet velocity was taken to be uniform and axial with no inlet boundary layer thickness.…”

Section: Meshes and Boundary Conditionsmentioning

confidence: 99%

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Dawes and Denton Codes Applied to a Transonic Compressor Rotor

Backström

1990

Volume 1: Turbomachinery

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The three-dimensional viscous transonic time marching Denton code L0SS3D, and Dawes code BTOB3D are applied to the first stage rotor of the NACA 5-stage transonic compressor. Computing time per solution on a mini-supercomputer was about 9 hours for a mesh of 65 000 points. LOSS3D predicted pressure ratio and loss distributions reasonably well at design point, but did not quite satisfy the convergence criteria. BT0B3D tended to overpredict the total pressure ratio over the outer half of span due to an underprediction of loss in the complicated separated flow region triggered by shock boundary layer interaction on the suction surface, but prediction was good at 90% speed where shock boundary layer interaction was less severe. The use of a computationally convenient excessively large tip clearance is not recommended when shock-boundary layer interaction is expected, especially at off-design conditions.

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Section: Btob3d With Tip Clearancementioning

confidence: 97%

Section: The Compressormentioning

confidence: 99%

Section: Experimental Datamentioning

confidence: 99%

Section: Meshes and Boundary Conditionsmentioning

confidence: 99%

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Dawes and Denton Codes Applied to a Transonic Compressor Rotor

Backström

1990

Volume 1: Turbomachinery

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“…The design and performance of this compressor may be found in a series of NACA reports 11,12,13,14 . The rotor blades are all double circular arc, as are the first two rows of stator blades, while the last three rows of stator blades are a modified NACA 65-series profile 15 . It is expected that the Aungier loss model, being based on cascade data for these types of airfoils, should be a good predictor of the performance map.…”

Section: Naca 5-stage Compressormentioning

confidence: 99%

Compressor Modeling and Simulation Using Object-Oriented Turbomachinery Analysis Code (OTAC)

Denney¹,

Kestner²,

Mavris³

2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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The objective of this research is to investigate the capabilities of OTAC as a compressor modeling tool suitable for conceptual design in an academic research environment. The investigation was carried out by modeling two multi-stage compressor models, the NACA 5-stage transonic compressor and the GE E3 high pressure compressor. For these models the Aungier compressor loss and deviation model was coded in several OTAC sub-elements.The NACA compressor, being very similar in design to the empirical data base used in the Aungier loss model, provided an excellent demonstration of the model capability. The effect of increasing the number of streamlines was observed generally to improve the accuracy of the loss prediction and the shape of the speedline characteristics.The E3 HPC, having numerous stages made up of more modern airfoil designs, required additional adjustment to the loss model. A process for identifying and adjusting several tuning factors was demonstrated. It was found that separating the loss matching from the velocity triangle matching facilitated the process. To accomplish this, the design point was first matched in "calibration mode", whereby the OTAC solver setup was modified to match the tangential velocities provided in the E3 design report which did not satisfy the simple radial equilibrium assumption of OTAC.While much work still remains to be done, this preliminary investigation has demonstrated that OTAC may be a useful teaching tool, bridging the gap between introductory engine cycle analysis courses and advanced turbomachinery analysis courses. The capability of the model also appears suitable for serious conceptual design applications within an integrated multidisciplinary design environment.

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The Emergence of the Turbofan Engine

Smith¹,

Mindell²

2000

Archimedes

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Aerodynamic Design and Performance of Five-Stage Transonic Axial-Flow Compressor

Cited by 6 publications

References 0 publications

Dawes and Denton Codes Applied to a Transonic Compressor Rotor

Dawes and Denton Codes Applied to a Transonic Compressor Rotor

Compressor Modeling and Simulation Using Object-Oriented Turbomachinery Analysis Code (OTAC)

The Emergence of the Turbofan Engine

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