Development of high performance oxidizer turbo-pump

J. Takida, K. Yoshikawa, A. Ogawara, M. Atsumi, Kazuyoshi Miyagawa, K. Kobayashi, T. Miyawaki

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

1 Citation (Scopus)

Abstract

In order to develop a high performance turbo-pump which consists of many components such as pump, turbine, bearings, shaft seals, etc., it is necessary not only to improve the performance of such component but also to reach good balance in performance and strength as a system, in other words, integration of performance and reliability is important. Efficiency of turbo-pump for rocket engines is generally around 30%, and its performance does not usually become a problem for the engine system. An important thing is to reduce an unstable dynamic load by cavitation of a pump. In addition, it is also important that there is an enough operation margin for components such as shaft seals and bearings. Mitsubishi Heavy Industries (MHI) has developed an oxidizer turbo-pump in the in-house research program. Through this development, new approach was tried for these problems. In this paper, the technical feature of this oxidizer turbo-pump and the results of component tests and turbo-pump tests are presented. The development approach for the oxidizer turbo-pump enabled achievement of the stable operation of the oxidizer turbo-pump in a short development period and few tests, and its effectiveness has demonstrated.

Original languageEnglish
Title of host publicationCollection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference
Pages4870-4876
Number of pages7
Volume5
Publication statusPublished - 2007
Externally publishedYes
Event43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference - Cincinnati, OH
Duration: 2007 Jul 82007 Jul 11

Other

Other43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference
CityCincinnati, OH
Period07/7/807/7/11

Fingerprint

oxidizers
pump
pumps
shaft
turbine pumps
engine
rocket engines
dynamic loads
cavitation flow
cavitation
engines
margins
research program
turbine
industries
industry

ASJC Scopus subject areas

  • Space and Planetary Science

Cite this

Takida, J., Yoshikawa, K., Ogawara, A., Atsumi, M., Miyagawa, K., Kobayashi, K., & Miyawaki, T. (2007). Development of high performance oxidizer turbo-pump. In Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference (Vol. 5, pp. 4870-4876)

Development of high performance oxidizer turbo-pump. / Takida, J.; Yoshikawa, K.; Ogawara, A.; Atsumi, M.; Miyagawa, Kazuyoshi; Kobayashi, K.; Miyawaki, T.

Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference. Vol. 5 2007. p. 4870-4876.

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

Takida, J, Yoshikawa, K, Ogawara, A, Atsumi, M, Miyagawa, K, Kobayashi, K & Miyawaki, T 2007, Development of high performance oxidizer turbo-pump. in Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference. vol. 5, pp. 4870-4876, 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Cincinnati, OH, 07/7/8.
Takida J, Yoshikawa K, Ogawara A, Atsumi M, Miyagawa K, Kobayashi K et al. Development of high performance oxidizer turbo-pump. In Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference. Vol. 5. 2007. p. 4870-4876
Takida, J. ; Yoshikawa, K. ; Ogawara, A. ; Atsumi, M. ; Miyagawa, Kazuyoshi ; Kobayashi, K. ; Miyawaki, T. / Development of high performance oxidizer turbo-pump. Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference. Vol. 5 2007. pp. 4870-4876
@inproceedings{0e448337512c4c0888b8ff14c84fc5f4,
title = "Development of high performance oxidizer turbo-pump",
abstract = "In order to develop a high performance turbo-pump which consists of many components such as pump, turbine, bearings, shaft seals, etc., it is necessary not only to improve the performance of such component but also to reach good balance in performance and strength as a system, in other words, integration of performance and reliability is important. Efficiency of turbo-pump for rocket engines is generally around 30{\%}, and its performance does not usually become a problem for the engine system. An important thing is to reduce an unstable dynamic load by cavitation of a pump. In addition, it is also important that there is an enough operation margin for components such as shaft seals and bearings. Mitsubishi Heavy Industries (MHI) has developed an oxidizer turbo-pump in the in-house research program. Through this development, new approach was tried for these problems. In this paper, the technical feature of this oxidizer turbo-pump and the results of component tests and turbo-pump tests are presented. The development approach for the oxidizer turbo-pump enabled achievement of the stable operation of the oxidizer turbo-pump in a short development period and few tests, and its effectiveness has demonstrated.",
author = "J. Takida and K. Yoshikawa and A. Ogawara and M. Atsumi and Kazuyoshi Miyagawa and K. Kobayashi and T. Miyawaki",
year = "2007",
language = "English",
isbn = "1563479036",
volume = "5",
pages = "4870--4876",
booktitle = "Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference",

}

TY - GEN

T1 - Development of high performance oxidizer turbo-pump

AU - Takida, J.

AU - Yoshikawa, K.

AU - Ogawara, A.

AU - Atsumi, M.

AU - Miyagawa, Kazuyoshi

AU - Kobayashi, K.

AU - Miyawaki, T.

PY - 2007

Y1 - 2007

N2 - In order to develop a high performance turbo-pump which consists of many components such as pump, turbine, bearings, shaft seals, etc., it is necessary not only to improve the performance of such component but also to reach good balance in performance and strength as a system, in other words, integration of performance and reliability is important. Efficiency of turbo-pump for rocket engines is generally around 30%, and its performance does not usually become a problem for the engine system. An important thing is to reduce an unstable dynamic load by cavitation of a pump. In addition, it is also important that there is an enough operation margin for components such as shaft seals and bearings. Mitsubishi Heavy Industries (MHI) has developed an oxidizer turbo-pump in the in-house research program. Through this development, new approach was tried for these problems. In this paper, the technical feature of this oxidizer turbo-pump and the results of component tests and turbo-pump tests are presented. The development approach for the oxidizer turbo-pump enabled achievement of the stable operation of the oxidizer turbo-pump in a short development period and few tests, and its effectiveness has demonstrated.

AB - In order to develop a high performance turbo-pump which consists of many components such as pump, turbine, bearings, shaft seals, etc., it is necessary not only to improve the performance of such component but also to reach good balance in performance and strength as a system, in other words, integration of performance and reliability is important. Efficiency of turbo-pump for rocket engines is generally around 30%, and its performance does not usually become a problem for the engine system. An important thing is to reduce an unstable dynamic load by cavitation of a pump. In addition, it is also important that there is an enough operation margin for components such as shaft seals and bearings. Mitsubishi Heavy Industries (MHI) has developed an oxidizer turbo-pump in the in-house research program. Through this development, new approach was tried for these problems. In this paper, the technical feature of this oxidizer turbo-pump and the results of component tests and turbo-pump tests are presented. The development approach for the oxidizer turbo-pump enabled achievement of the stable operation of the oxidizer turbo-pump in a short development period and few tests, and its effectiveness has demonstrated.

UR - http://www.scopus.com/inward/record.url?scp=36749030604&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=36749030604&partnerID=8YFLogxK

M3 - Conference contribution

SN - 1563479036

SN - 9781563479038

VL - 5

SP - 4870

EP - 4876

BT - Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference

ER -