Effect of mainstream velocity on the heat transfer coefficient of gas turbine blade tips

Jin Young Jeong; Woojun Kim; Jae Su Kwak; Byung Ju Lee; Jin Taek Chung

doi:10.3390/en14237968

Effect of mainstream velocity on the heat transfer coefficient of gas turbine blade tips

Jin Young Jeong, Woojun Kim, Jae Su Kwak, Byung Ju Lee, Jin Taek Chung

Research output: Contribution to journal › Article › peer-review

1 Citation (Scopus)

Abstract

This study experimentally investigated the effects of cascade inlet velocity on the distribution and the level of the heat transfer coefficient on a gas turbine blade tip. The tests were conducted in a transient turbine test facility at Korea Aerospace University, and three cascade inlet velocities—30, 60, and 90 m/s—were considered. The heat transfer coefficient was measured using the transient IR camera technique with a linear regression method, and both the squealer and plane tips were investigated. The results showed that the overall averaged heat transfer coefficient was generally proportional to the inlet velocity. As the inlet velocity is increased from 30 m/s to 60 m/s and 90 m/s, the heat transfer coefficient increased by 11.4% and 25.0% for plane tip, and 26.6% and 64.1% for squealer tip, respectively. However, the heat transfer coefficient near the leading edge of the squealer tip and the reattachment region of the plane tip was greatly affected by the cascade inlet velocity. Therefore, heat transfer experiments for a gas turbine blade tip should be performed under engine simulating conditions.

Original language	English
Article number	7968
Journal	Energies
Volume	14
Issue number	23
DOIs	https://doi.org/10.3390/en14237968
Publication status	Published - 2021 Dec 1

Bibliographical note

Funding Information:
For the plane tip, the size of the vortex near the blade mid-chord increased as the inlet mainstream velocity increased, resulting in a significant increase in heat trans-fer.but the local HTC, particularly in the frontal region, was greatly affected by the inlet 3. The overall averaged HTC tended to be proportional to the inlet mainstream velocity, but the local HTC, particularly in the frontal region, was greatly affected by the inlet mainstream velocity. Therefore, experimental studies should be conducted under en-Authorgine Contributions:simulating condiConceptualization,tions. J.Y.J., J.S.K. and J.T.C.; methodology, J.Y.J. and W.K.; software, J.Y.J. and B.J.L.; validation, J.Y.J., W.K. and B.J.L.; formal analysis, J.Y.J. and J.S.K.; investi- Author Contributions: Conceptualization, J.Y.J., J.S.K. and J.T.C.; methodology, J.Y.J. and W.K.; software, J.Y.J. and B.J.L.; validation, J.Y.J., W.K. and B.J.L.; formal analysis, J.Y.J. and J.S.K.; investigation, J.Y.J. and W.K.; resources, J.S.K. and J.T.C.; data curation, J.Y.J. and W.K.; writing—original draft preparation, J.Y.J. and J.S.K.; writing—review and editing, J.Y.J. and J.S.K.; visualization, J.Y.J.; supervision, J.S.K.; project administration, J.S.K. and J.T.C.; funding acquisition, J.S.K. and J.T.C. All authFunding:ors have Thisread workandhasagrbeeneed to supportedthe publishbyedtheversiUon ofAV Highthe manuEfficiencyscript.Turbine Research Center program of the Defense Acquisition Program Administration and Agency for Defense Development. Funding: This work has been supported by the UAV High Efficiency Turbine Research Center program of the Defense Acquisition Program Administration and Agency for Defense Development.

Funding Information:
authorsFunding:haveThisreadworkandhasagreedbeentosupportedthe publishedby theversionUAVofHighthe manuscript.Efficiency Turbine Research Center program of the Defense Acquisition Program Administration and Agency for Defense Development. Funding: This work has been supported by the UAV High Efficiency Turbine Research Center pro-.

Publisher Copyright:
© 2021 by the authors. Licensee MDPI, Basel, Switzerland.

Keywords

Blade tip
Gas turbine
Heat transfer
High speed condition

ASJC Scopus subject areas

Renewable Energy, Sustainability and the Environment
Fuel Technology
Energy Engineering and Power Technology
Energy (miscellaneous)
Control and Optimization
Electrical and Electronic Engineering

UN SDGs

This output contributes to the following UN Sustainable Development Goals (SDGs)

Access to Document

10.3390/en14237968

Cite this

@article{b184435b27ad41d3bcbf605b1f364b4c,

title = "Effect of mainstream velocity on the heat transfer coefficient of gas turbine blade tips",

abstract = "This study experimentally investigated the effects of cascade inlet velocity on the distribution and the level of the heat transfer coefficient on a gas turbine blade tip. The tests were conducted in a transient turbine test facility at Korea Aerospace University, and three cascade inlet velocities—30, 60, and 90 m/s—were considered. The heat transfer coefficient was measured using the transient IR camera technique with a linear regression method, and both the squealer and plane tips were investigated. The results showed that the overall averaged heat transfer coefficient was generally proportional to the inlet velocity. As the inlet velocity is increased from 30 m/s to 60 m/s and 90 m/s, the heat transfer coefficient increased by 11.4% and 25.0% for plane tip, and 26.6% and 64.1% for squealer tip, respectively. However, the heat transfer coefficient near the leading edge of the squealer tip and the reattachment region of the plane tip was greatly affected by the cascade inlet velocity. Therefore, heat transfer experiments for a gas turbine blade tip should be performed under engine simulating conditions.",

keywords = "Blade tip, Gas turbine, Heat transfer, High speed condition",

author = "Jeong, {Jin Young} and Woojun Kim and Kwak, {Jae Su} and Lee, {Byung Ju} and Chung, {Jin Taek}",

note = "Funding Information: For the plane tip, the size of the vortex near the blade mid-chord increased as the inlet mainstream velocity increased, resulting in a significant increase in heat trans-fer.but the local HTC, particularly in the frontal region, was greatly affected by the inlet 3. The overall averaged HTC tended to be proportional to the inlet mainstream velocity, but the local HTC, particularly in the frontal region, was greatly affected by the inlet mainstream velocity. Therefore, experimental studies should be conducted under en-Authorgine Contributions:simulating condiConceptualization,tions. J.Y.J., J.S.K. and J.T.C.; methodology, J.Y.J. and W.K.; software, J.Y.J. and B.J.L.; validation, J.Y.J., W.K. and B.J.L.; formal analysis, J.Y.J. and J.S.K.; investi- Author Contributions: Conceptualization, J.Y.J., J.S.K. and J.T.C.; methodology, J.Y.J. and W.K.; software, J.Y.J. and B.J.L.; validation, J.Y.J., W.K. and B.J.L.; formal analysis, J.Y.J. and J.S.K.; investigation, J.Y.J. and W.K.; resources, J.S.K. and J.T.C.; data curation, J.Y.J. and W.K.; writing—original draft preparation, J.Y.J. and J.S.K.; writing—review and editing, J.Y.J. and J.S.K.; visualization, J.Y.J.; supervision, J.S.K.; project administration, J.S.K. and J.T.C.; funding acquisition, J.S.K. and J.T.C. All authFunding:ors have Thisread workandhasagrbeeneed to supportedthe publishbyedtheversiUon ofAV Highthe manuEfficiencyscript.Turbine Research Center program of the Defense Acquisition Program Administration and Agency for Defense Development. Funding: This work has been supported by the UAV High Efficiency Turbine Research Center program of the Defense Acquisition Program Administration and Agency for Defense Development. Funding Information: authorsFunding:haveThisreadworkandhasagreedbeentosupportedthe publishedby theversionUAVofHighthe manuscript.Efficiency Turbine Research Center program of the Defense Acquisition Program Administration and Agency for Defense Development. Funding: This work has been supported by the UAV High Efficiency Turbine Research Center pro-. Publisher Copyright: {\textcopyright} 2021 by the authors. Licensee MDPI, Basel, Switzerland.",

year = "2021",

month = dec,

day = "1",

doi = "10.3390/en14237968",

language = "English",

volume = "14",

journal = "Energies",

issn = "1996-1073",

publisher = "Multidisciplinary Digital Publishing Institute (MDPI)",

number = "23",

}

TY - JOUR

T1 - Effect of mainstream velocity on the heat transfer coefficient of gas turbine blade tips

AU - Jeong, Jin Young

AU - Kim, Woojun

AU - Kwak, Jae Su

AU - Lee, Byung Ju

AU - Chung, Jin Taek

N1 - Funding Information: For the plane tip, the size of the vortex near the blade mid-chord increased as the inlet mainstream velocity increased, resulting in a significant increase in heat trans-fer.but the local HTC, particularly in the frontal region, was greatly affected by the inlet 3. The overall averaged HTC tended to be proportional to the inlet mainstream velocity, but the local HTC, particularly in the frontal region, was greatly affected by the inlet mainstream velocity. Therefore, experimental studies should be conducted under en-Authorgine Contributions:simulating condiConceptualization,tions. J.Y.J., J.S.K. and J.T.C.; methodology, J.Y.J. and W.K.; software, J.Y.J. and B.J.L.; validation, J.Y.J., W.K. and B.J.L.; formal analysis, J.Y.J. and J.S.K.; investi- Author Contributions: Conceptualization, J.Y.J., J.S.K. and J.T.C.; methodology, J.Y.J. and W.K.; software, J.Y.J. and B.J.L.; validation, J.Y.J., W.K. and B.J.L.; formal analysis, J.Y.J. and J.S.K.; investigation, J.Y.J. and W.K.; resources, J.S.K. and J.T.C.; data curation, J.Y.J. and W.K.; writing—original draft preparation, J.Y.J. and J.S.K.; writing—review and editing, J.Y.J. and J.S.K.; visualization, J.Y.J.; supervision, J.S.K.; project administration, J.S.K. and J.T.C.; funding acquisition, J.S.K. and J.T.C. All authFunding:ors have Thisread workandhasagrbeeneed to supportedthe publishbyedtheversiUon ofAV Highthe manuEfficiencyscript.Turbine Research Center program of the Defense Acquisition Program Administration and Agency for Defense Development. Funding: This work has been supported by the UAV High Efficiency Turbine Research Center program of the Defense Acquisition Program Administration and Agency for Defense Development. Funding Information: authorsFunding:haveThisreadworkandhasagreedbeentosupportedthe publishedby theversionUAVofHighthe manuscript.Efficiency Turbine Research Center program of the Defense Acquisition Program Administration and Agency for Defense Development. Funding: This work has been supported by the UAV High Efficiency Turbine Research Center pro-. Publisher Copyright: © 2021 by the authors. Licensee MDPI, Basel, Switzerland.

PY - 2021/12/1

Y1 - 2021/12/1

N2 - This study experimentally investigated the effects of cascade inlet velocity on the distribution and the level of the heat transfer coefficient on a gas turbine blade tip. The tests were conducted in a transient turbine test facility at Korea Aerospace University, and three cascade inlet velocities—30, 60, and 90 m/s—were considered. The heat transfer coefficient was measured using the transient IR camera technique with a linear regression method, and both the squealer and plane tips were investigated. The results showed that the overall averaged heat transfer coefficient was generally proportional to the inlet velocity. As the inlet velocity is increased from 30 m/s to 60 m/s and 90 m/s, the heat transfer coefficient increased by 11.4% and 25.0% for plane tip, and 26.6% and 64.1% for squealer tip, respectively. However, the heat transfer coefficient near the leading edge of the squealer tip and the reattachment region of the plane tip was greatly affected by the cascade inlet velocity. Therefore, heat transfer experiments for a gas turbine blade tip should be performed under engine simulating conditions.

AB - This study experimentally investigated the effects of cascade inlet velocity on the distribution and the level of the heat transfer coefficient on a gas turbine blade tip. The tests were conducted in a transient turbine test facility at Korea Aerospace University, and three cascade inlet velocities—30, 60, and 90 m/s—were considered. The heat transfer coefficient was measured using the transient IR camera technique with a linear regression method, and both the squealer and plane tips were investigated. The results showed that the overall averaged heat transfer coefficient was generally proportional to the inlet velocity. As the inlet velocity is increased from 30 m/s to 60 m/s and 90 m/s, the heat transfer coefficient increased by 11.4% and 25.0% for plane tip, and 26.6% and 64.1% for squealer tip, respectively. However, the heat transfer coefficient near the leading edge of the squealer tip and the reattachment region of the plane tip was greatly affected by the cascade inlet velocity. Therefore, heat transfer experiments for a gas turbine blade tip should be performed under engine simulating conditions.

KW - Blade tip

KW - Gas turbine

KW - Heat transfer

KW - High speed condition

UR - http://www.scopus.com/inward/record.url?scp=85120304706&partnerID=8YFLogxK

U2 - 10.3390/en14237968

DO - 10.3390/en14237968

M3 - Article

AN - SCOPUS:85120304706

SN - 1996-1073

VL - 14

JO - Energies

JF - Energies

IS - 23

M1 - 7968

ER -

Effect of mainstream velocity on the heat transfer coefficient of gas turbine blade tips

Abstract

Bibliographical note

Keywords

ASJC Scopus subject areas

UN SDGs

Access to Document

Other files and links

Fingerprint

Cite this