Experimental Investigation of the Flow Field in a Multistage Axial Flow Compressor

Lakshminarayana, B.; Suryavamshi, N.; Prato, J.; Moritz, Robert R.

doi:10.1155/s1023621x96000127

Cited by 4 publications

(5 citation statements)

References 5 publications

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“…The efficiency values are similar to those illustrated by Lakshminarayana et al [1]. The values of V a /V a RE are the axial velocities as a ratio to the axial velocity if the total pressure was radially constant.…”

Section: A Conventional Stagesupporting

confidence: 86%

“…Thus designing for a constant enthalpy rise implies a constant spanwise stage pressure rise. This is inconsistent with experimental evidence, which indicates that the efficiency falls significantly towards the annulus walls and is a maximum near the midspan of the blades, as shown by Lakshminarayana et al [1]. Thus, for a constant spanwise pressure rise, the design enthalpy rise will need to be a maximum at the blade ends and a minimum near the midspan.…”

Section: Basis Of the Methodsmentioning

confidence: 75%

“…An experimental investigation would be essential before the design method could be applied with confidence to a production compressor. Such an investigation could be most reliably and economically conducted on a low speed multistage research machine, such as the one described by Robinson [8] or that used by Lakshminarayana et al [1].…”

Section: Discussionmentioning

confidence: 99%

See 2 more Smart Citations

The design and performance of axial compressor stages in fully developmed flow

McKenzie

2000

Proceedings of the Institution of Mechanical Engineers, Part A:

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A design method for axial compressor stages is presented which is indicated to reduce the tendency for efficiency to diminish as the design work coefficient increases. Three worked examples with different levels of design work coefficient are used to demonstrate the potential advantages of the procedure. If experimentally confirmed, the results would be of value in situations where the blade speed is restricted, as in the case of core compressor stages attached to the fan shaft of turbofan aero engines. Another potential field of application is the compression of such gases as helium and hydrogen, where the speed of sound is high and mechanical limitations to the blade speed restrict the Mach numbers and therefore the stage pressure ratio achievable with conventional levels of work coefficient.

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Section: A Conventional Stagesupporting

confidence: 86%

Section: Basis Of the Methodsmentioning

confidence: 75%

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The design and performance of axial compressor stages in fully developmed flow

McKenzie

2000

Proceedings of the Institution of Mechanical Engineers, Part A:

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“…The traverse can be axially moved such that area traverses can be conducted downstream of stators 2 and 3 and rotor 3. Lakshminarayana et al [5] provided a complete description of the test compressor, associated instrumentation, operating characteristics, blade pro le geometries and area traverse locations.…”

Section: Test Facility Instrumentation and Data Acquisition Systemmentioning

confidence: 99%

Three-dimensional flow field downstream of an embedded stator in a multistage axial flow compressor: Part 1: Steady and unsteady flow fields

Prato

Lakshminarayana

Suryavamshi

2001

Proceedings of the Institution of Mechanical Engineers, Part A:

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A comprehensive investigation of the three-dimensional unsteady ow and thermal eld downstream of an embedded stator in a multistage compressor, acquired with a high-response hot-lm probe and aspirating probe, is presented and analysed. Some of the earlier data (from a ve-hole probe and a high-response Kulite probe) from the same compressor is used with the present data to provide an integrated interpretation of the ow and thermal elds. Part 1 includes a brief description of the facility, the development of the hot-lm technique for the multistage ow eld measurement and an interpretation of the various ow eld features, such as the hub clearance ow and the suction surfacecasing end-wall corner region. Part 2 covers velocity-velocity and velocity-temperature correlations and the assessment of their magnitudes in the average-passage equations. The results presented in this part of the paper (Part 1) indicate that major blockage in the stator hub end wall is caused by leakage ow and its possible subsequent roll-up into a vortex. Similar features exist in the suction surface casing end-wall corner due to secondary ow and its interaction with the upstream rotor end-wall ow. These are also the regions with the highest levels of unsteadiness. The transport of rotor wake towards the pressure side of the stator is con rmed. Both the revolution and the blade periodic velocity uctuations are found to be signi cantly greater than the aperiodic uctuations.

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“…The low speed and the large dimensions of the rig allow for better spatial and time resolution of the measurements and a wider range of experimental methods, including hot-wire anemometry and oil-flow visualization, which are rarely available at the full-speed machines on-site. Lakshminarayana et al (1996) carried out a similar approach to the compressor with a tip Mach number of 0.5, but the rig was intentionally made for research purposes with sufficient axial gaps and possible pitchwise motion of the probe, so the spanwise distributions were obtained as pitchwise averaged values at each immersion distance, and no corrections were applied to the measured values.…”

Section: Introductionmentioning

confidence: 99%

A flow field around a cylindrical probe in proximity to stator blades and its effect on the measurements

Sedunin

Kalinin

et al. 2023

J. Phys.: Conf. Ser.

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In multistage axial compressors of gas turbine engines, there is a need for a detailed understanding of the flow field in between the blade rows, which could be obtained by spanwise traversing. This requires a pneumatic probe to be immersed into the flow path between the blade rows, where the space is limited. Therefore, the probe will affect the flow field around it and in the blade channel, and the probe readings will be affected by that flow field. As a result, these probe readings cannot be translated to flow parameters based on just the freestream calibration characteristics, obtained in the idealized wind tunnel. In our paper, we provide a computational analysis of the flow field around the cylindrical probe in a constrained inter-blade-row environment at different circumferential locations and flow conditions both upstream and downstream of the stator blade row. It is shown that the flow angle measurement error can reach up to five degrees in the mid-pitch locations compared to undistorted flow, and dynamic head measurements can be up to 30% away from the actual mean values of the flow. These deviations are shown to be caused by flow field interaction inside the blade channel and, as a result, measured values, obtained during industrial compressor testing, could be corrected accordingly. The universal correction procedure is proposed for further use in the industry

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Experimental Investigation of the Flow Field in a Multistage Axial Flow Compressor

Cited by 4 publications

References 5 publications

The design and performance of axial compressor stages in fully developmed flow

The design and performance of axial compressor stages in fully developmed flow

Three-dimensional flow field downstream of an embedded stator in a multistage axial flow compressor: Part 1: Steady and unsteady flow fields

A flow field around a cylindrical probe in proximity to stator blades and its effect on the measurements

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