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Research Papers

Study on Advanced Internal Cooling Technologies for the Development of Next-Generation Small-Class Aircraft Engines

[+] Author and Article Information
Shu Fujimoto

 IHI Corporation, Tokyo 190-1297, Japansyuu_fujimoto@ihi.co.jp

Yoji Okita

 IHI Corporation, Tokyo 190-1297, Japan

Yoshitaka Fukuyama, Takashi Yamane, Fujio Mimura, Masahiro Matsushita

 Japan Aerospace Exploration Agency, Tokyo 182-8522, Japan

Toyoaki Yoshida

 Tokyo University of Agriculture and Technology, Tokyo 184-8588, Japan

J. Turbomach 132(3), 031019 (Apr 07, 2010) (10 pages) doi:10.1115/1.3151602 History: Received December 25, 2008; Revised January 28, 2009; Published April 07, 2010; Online April 07, 2010

An innovative internal cooling structure named multislot cooling has been invented for high-pressure turbine (HPT) nozzles and blades. This cooling structure has been designed to be simple and inexpensive and to exhibit good cooling performance. In order to confirm the cooling performance of this structure, test pieces of dummy turbine nozzles were manufactured. Three geometric parameters (width of slots, overall height of cooling channel, and height of jet impingement) are associated with these test pieces. The cooling performance tests were conducted by using these test pieces for several Reynolds numbers of the mainstream hot gas [2.2×1053.4×105] and cooling airflow [3×1031×104]. Infrared images of the heated surfaces of the test pieces were captured for every Reynolds number in the tests, and then the distributions of the cooling effectiveness were obtained. Simultaneously, the pressure losses were measured. This paper describes the hot gas flow tests performed to confirm the effects of the geometric parameters on the cooling performance and pressure loss, and to obtain data of Nusselt number and pressure loss coefficient for the design of turbine nozzles in the future by applying this new cooling structure to next-generation small-class aircraft engines. Additionally a preliminary analysis of airfoil cooling was performed to evaluate both cooling performance of conventional impingement cooling and multislot cooling when applied to a HPT nozzle. As a result it was found that the multislot cooling is well applicable to cooling of HPT airfoils.

Copyright © 2010 by American Society of Mechanical Engineers
Topics: Cooling , Pressure , Nozzles
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Figures

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Figure 1

Cross-sectional drawing of the conventional cooling nozzle (12)

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Figure 2

Schematic of the cooling flow in the conventional cooling nozzle

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Figure 3

Image of a turbine nozzle to which the multislot cooling structure can be applied: (a) overall view of a turbine nozzle and (b) cut model of turbine nozzle

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Figure 4

Schematic of the test facility for the basic cooling performance test

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Figure 5

Schematic of the test rig for the basic cooling performance test

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Figure 6

Schematic of a test piece for the basic cooling performance test: (a) side view of a test piece and (b) top view of a test piece (a part of stainless steel)

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Figure 7

Example of the temperature field captured by the IR camera under typical conditions

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Figure 8

Example of the cooling effectiveness distribution on a test piece

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Figure 9

Dependence on the overall height of the cooling passage (Z): (a) local cooling effectiveness at the center of the test piece and (b) pressure loss coefficient of the entire cooling passage

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Figure 10

Dependence on the impingement height (H). (a) Local cooling effectiveness at the center of the test piece. (b) Pressure loss coefficient of the entire cooling passage. (c) Cooling effectiveness versus nondimensional pressure loss.

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Figure 11

Dependence on the impingement slot width (W). (a) Local cooling effectiveness at the center of the test piece. (b) Pressure loss coefficient of the entire cooling passage. (c) Cooling effectiveness versus nondimensional pressure loss.

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Figure 12

Averaged Nusselt number of the heated surfaces of the test pieces Nug¯ versus Reynolds number Reg

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Figure 13

Averaged Nusselt number of the multislot cooling NucW¯ versus Reynolds number RecW

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Figure 14

Averaged Nusselt number of multislot cooling NucDh¯ versus Reynolds number RecDh

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Figure 15

Pressure loss coefficient per 180 deg turn of multislot cooling versus Reynolds number RecDh

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Figure 16

Preliminary analysis models of airfoil cooling: (a) overall view, (b) cross-sectional drawing of multislot cooling, and (c) cross-sectional drawing of conventional impingement cooling

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Figure 17

Averaged cooling effectiveness η¯ versus nondimensional pressure loss

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