Effects of multi-section swirl injection method on fuel regression rate of high density polyethylene fueled hybrid rocket engine

Sho Ohyama; Y. Hirata; K. Araki; K. Ohe; Shigeru Aso; Yasuhiro Tani; T. Shimada

Effects of multi-section swirl injection method on fuel regression rate of high density polyethylene fueled hybrid rocket engine

Sho Ohyama, Y. Hirata, K. Araki, K. Ohe, Shigeru Aso, Yasuhiro Tani, T. Shimada

Space Systems Engineering

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

1 Citation (Scopus)

Abstract

Low fuel regression rate is fatal disadvantage for hybrid rocket. To overcome this problem, a lot of methods have been proposed. In Kyushu university multi-section swirl injection method has been proposed to increase the fuel regression rate and combustion efficiency. This method generates swirling flow in combustion chamber through injector ports located on the some cross-sections over a fuel grain. High density polyethylene and gaseous oxygen were used as propellant. Multi-section swirl injection method shows twice higher fuel regression rate than that of the conventional method with no swirl in the previous study. In the present study, the effects of the number and the diameter of injector ports was investigated under constant total injector ports area condition. To decrease interference of oxidizer flow, the average regression rate increased at low oxidizer mass flux region.

Original language	English
Title of host publication	49th AIAA/ASME/SAE/ASEE Joint PropulsionConference
Publication status	Published - Sep 16 2013
Event	49th AIAA/ASME/SAE/ASEE Joint PropulsionConference - San Jose, CA, United States Duration: Jul 14 2013 → Jul 17 2013

Publication series

Name	49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

Other

Other	49th AIAA/ASME/SAE/ASEE Joint PropulsionConference
Country	United States
City	San Jose, CA
Period	7/14/13 → 7/17/13

All Science Journal Classification (ASJC) codes

Aerospace Engineering
Control and Systems Engineering
Electrical and Electronic Engineering

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Effects of multi-section swirl injection method on fuel regression rate of high density polyethylene fueled hybrid rocket engine. / Ohyama, Sho; Hirata, Y.; Araki, K.; Ohe, K.; Aso, Shigeru; Tani, Yasuhiro; Shimada, T.

49th AIAA/ASME/SAE/ASEE Joint PropulsionConference. 2013. (49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

Ohyama, S, Hirata, Y, Araki, K, Ohe, K, Aso, S, Tani, Y & Shimada, T 2013, Effects of multi-section swirl injection method on fuel regression rate of high density polyethylene fueled hybrid rocket engine. in 49th AIAA/ASME/SAE/ASEE Joint PropulsionConference. 49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, 49th AIAA/ASME/SAE/ASEE Joint PropulsionConference, San Jose, CA, United States, 7/14/13.

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title = "Effects of multi-section swirl injection method on fuel regression rate of high density polyethylene fueled hybrid rocket engine",

abstract = "Low fuel regression rate is fatal disadvantage for hybrid rocket. To overcome this problem, a lot of methods have been proposed. In Kyushu university multi-section swirl injection method has been proposed to increase the fuel regression rate and combustion efficiency. This method generates swirling flow in combustion chamber through injector ports located on the some cross-sections over a fuel grain. High density polyethylene and gaseous oxygen were used as propellant. Multi-section swirl injection method shows twice higher fuel regression rate than that of the conventional method with no swirl in the previous study. In the present study, the effects of the number and the diameter of injector ports was investigated under constant total injector ports area condition. To decrease interference of oxidizer flow, the average regression rate increased at low oxidizer mass flux region.",

author = "Sho Ohyama and Y. Hirata and K. Araki and K. Ohe and Shigeru Aso and Yasuhiro Tani and T. Shimada",

year = "2013",

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note = "49th AIAA/ASME/SAE/ASEE Joint PropulsionConference ; Conference date: 14-07-2013 Through 17-07-2013",

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T1 - Effects of multi-section swirl injection method on fuel regression rate of high density polyethylene fueled hybrid rocket engine

AU - Ohyama, Sho

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AU - Araki, K.

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AU - Aso, Shigeru

AU - Tani, Yasuhiro

AU - Shimada, T.

PY - 2013/9/16

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N2 - Low fuel regression rate is fatal disadvantage for hybrid rocket. To overcome this problem, a lot of methods have been proposed. In Kyushu university multi-section swirl injection method has been proposed to increase the fuel regression rate and combustion efficiency. This method generates swirling flow in combustion chamber through injector ports located on the some cross-sections over a fuel grain. High density polyethylene and gaseous oxygen were used as propellant. Multi-section swirl injection method shows twice higher fuel regression rate than that of the conventional method with no swirl in the previous study. In the present study, the effects of the number and the diameter of injector ports was investigated under constant total injector ports area condition. To decrease interference of oxidizer flow, the average regression rate increased at low oxidizer mass flux region.

AB - Low fuel regression rate is fatal disadvantage for hybrid rocket. To overcome this problem, a lot of methods have been proposed. In Kyushu university multi-section swirl injection method has been proposed to increase the fuel regression rate and combustion efficiency. This method generates swirling flow in combustion chamber through injector ports located on the some cross-sections over a fuel grain. High density polyethylene and gaseous oxygen were used as propellant. Multi-section swirl injection method shows twice higher fuel regression rate than that of the conventional method with no swirl in the previous study. In the present study, the effects of the number and the diameter of injector ports was investigated under constant total injector ports area condition. To decrease interference of oxidizer flow, the average regression rate increased at low oxidizer mass flux region.

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