Quantifying blockage in a multistage compressor for different tip clearances using steady and unsteady pressure measurements

Reid Adam Berdanier, Nicole L. Key

    Research output: Chapter in Book/Report/Conference proceedingConference contribution

    1 Citation (Scopus)

    Abstract

    With future gas turbine designs seeking increased overall pressure ratios, blade heights in the rear stages of high-pressure compressors are expected to decrease. As this will lead to an increase of relative tip clearance height, a detailed knowledge of the associated rotor tip leakage flows becomes increasingly important. In particular, the development of blockage due to large tip leakage flows can be an key component leading to an understanding of stage matching for multistage machines. To assess blockage related to increased tip clearance, a series of measurements are presented here from a three-stage compressor at two loading conditions on the 100% corrected speedline. These data correspond to three tip clearance configurations, up to 4% span. Initially, three-component velocities measured using hot-wire anemometry are analyzed. Following these initial calculations, a blockage definition technique related to gradient identification is introduced, by which the tip leakage flow size downstream of the rotors is directly related to the blockage in the tip region of the compressor. Further, steady pressures are used to calculate an approximate blockage downstream of the stators. Ultimately, these simplified pressure-based blockage calculation techniques reveal results which compare well with the velocity-based results, within three percent or better.

    Original languageEnglish (US)
    Title of host publication54th AIAA Aerospace Sciences Meeting
    PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
    ISBN (Print)9781624103933
    StatePublished - Jan 1 2016
    Event54th AIAA Aerospace Sciences Meeting, 2016 - San Diego, United States
    Duration: Jan 4 2016Jan 8 2016

    Publication series

    Name54th AIAA Aerospace Sciences Meeting

    Other

    Other54th AIAA Aerospace Sciences Meeting, 2016
    CountryUnited States
    CitySan Diego
    Period1/4/161/8/16

    Fingerprint

    Pressure measurement
    Compressors
    Rotors
    Stators
    Gas turbines
    Wire

    All Science Journal Classification (ASJC) codes

    • Aerospace Engineering

    Cite this

    Berdanier, R. A., & Key, N. L. (2016). Quantifying blockage in a multistage compressor for different tip clearances using steady and unsteady pressure measurements. In 54th AIAA Aerospace Sciences Meeting (54th AIAA Aerospace Sciences Meeting). American Institute of Aeronautics and Astronautics Inc, AIAA.
    Berdanier, Reid Adam ; Key, Nicole L. / Quantifying blockage in a multistage compressor for different tip clearances using steady and unsteady pressure measurements. 54th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc, AIAA, 2016. (54th AIAA Aerospace Sciences Meeting).
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    title = "Quantifying blockage in a multistage compressor for different tip clearances using steady and unsteady pressure measurements",
    abstract = "With future gas turbine designs seeking increased overall pressure ratios, blade heights in the rear stages of high-pressure compressors are expected to decrease. As this will lead to an increase of relative tip clearance height, a detailed knowledge of the associated rotor tip leakage flows becomes increasingly important. In particular, the development of blockage due to large tip leakage flows can be an key component leading to an understanding of stage matching for multistage machines. To assess blockage related to increased tip clearance, a series of measurements are presented here from a three-stage compressor at two loading conditions on the 100{\%} corrected speedline. These data correspond to three tip clearance configurations, up to 4{\%} span. Initially, three-component velocities measured using hot-wire anemometry are analyzed. Following these initial calculations, a blockage definition technique related to gradient identification is introduced, by which the tip leakage flow size downstream of the rotors is directly related to the blockage in the tip region of the compressor. Further, steady pressures are used to calculate an approximate blockage downstream of the stators. Ultimately, these simplified pressure-based blockage calculation techniques reveal results which compare well with the velocity-based results, within three percent or better.",
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    Berdanier, RA & Key, NL 2016, Quantifying blockage in a multistage compressor for different tip clearances using steady and unsteady pressure measurements. in 54th AIAA Aerospace Sciences Meeting. 54th AIAA Aerospace Sciences Meeting, American Institute of Aeronautics and Astronautics Inc, AIAA, 54th AIAA Aerospace Sciences Meeting, 2016, San Diego, United States, 1/4/16.

    Quantifying blockage in a multistage compressor for different tip clearances using steady and unsteady pressure measurements. / Berdanier, Reid Adam; Key, Nicole L.

    54th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc, AIAA, 2016. (54th AIAA Aerospace Sciences Meeting).

    Research output: Chapter in Book/Report/Conference proceedingConference contribution

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    N2 - With future gas turbine designs seeking increased overall pressure ratios, blade heights in the rear stages of high-pressure compressors are expected to decrease. As this will lead to an increase of relative tip clearance height, a detailed knowledge of the associated rotor tip leakage flows becomes increasingly important. In particular, the development of blockage due to large tip leakage flows can be an key component leading to an understanding of stage matching for multistage machines. To assess blockage related to increased tip clearance, a series of measurements are presented here from a three-stage compressor at two loading conditions on the 100% corrected speedline. These data correspond to three tip clearance configurations, up to 4% span. Initially, three-component velocities measured using hot-wire anemometry are analyzed. Following these initial calculations, a blockage definition technique related to gradient identification is introduced, by which the tip leakage flow size downstream of the rotors is directly related to the blockage in the tip region of the compressor. Further, steady pressures are used to calculate an approximate blockage downstream of the stators. Ultimately, these simplified pressure-based blockage calculation techniques reveal results which compare well with the velocity-based results, within three percent or better.

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    Berdanier RA, Key NL. Quantifying blockage in a multistage compressor for different tip clearances using steady and unsteady pressure measurements. In 54th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc, AIAA. 2016. (54th AIAA Aerospace Sciences Meeting).