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Research and development of cooled turbine for aircraft engines. Koku engine yo reikyaku turbine no kenkyu kaihatsu

Journal Article:

Abstract

For the turbine which is one of the principal elements of aircraft engine, progress in turbine use material development and cooling performance further heightened for the turbine are needed to grapple with the required heightening of turbine inlet temperature. In the present paper based on the turbine inlet temperature designed to be 1600[degree]C as a target, a two-dimensional model used for the turbine cooling performance test was structurally given together with the result of the above test which aimed at confirming the design calculation. As a result of cooling design for the turbine which was about 1600[degree]C in inlet temperature, the highest gas temperature was 1890 and 1470[degree]C on the stator blade and rotor blade, respectively. Both those blades were 0.66 and 0.62, respectively in cooling efficiency. To test the cooling performance, a two-dimensional cascade was tested with a doubly amplified model of cooling blade, the use of which could set its Reynolds number near that of the actual one. As compared with the actual operation, the test was made at low temperatures of 400 to 500[degree]C and low pressures of 0.02 to 0.03MPa. The test agreed with the design calculation in result. 4 refs., 8 figs.
Authors:
Maya, T; Yamawaki, S [1] 
  1. Ishikawajima-Harima Heavy Industries, Co. Ltd., Tokyo (Japan)
Publication Date:
May 01, 1994
Product Type:
Journal Article
Reference Number:
NEDO-94-920315; EDB-95-008034
Resource Relation:
Journal Name: Ishikawajima-Harima Giho (Ishikawajima-Harima Engineering Review); (Japan); Journal Volume: 34:3
Subject:
32 ENERGY CONSERVATION, CONSUMPTION, AND UTILIZATION; 33 ADVANCED PROPULSION SYSTEMS; 42 ENGINEERING; COOLING SYSTEMS; MECHANICAL STRUCTURES; SIMULATORS; TWO-DIMENSIONAL CALCULATIONS; TURBINES; INTAKE STRUCTURES; MATERIALS; TEMPERATURE DEPENDENCE; TEMPERATURE RANGE 1000-4000 K; TURBOFAN ENGINES; AIRCRAFT; ALIGNMENT; COMPUTERIZED SIMULATION; GASES; LIMITING VALUES; REYNOLDS NUMBER; SCALE MODELS; THERMAL EFFICIENCY; TURBINE BLADES; ANALOG SYSTEMS; EFFICIENCY; ENERGY SYSTEMS; ENGINES; EQUIPMENT; FLUIDS; FUNCTIONAL MODELS; HEAT ENGINES; INTERNAL COMBUSTION ENGINES; MACHINERY; SIMULATION; STRUCTURAL MODELS; TEMPERATURE RANGE; TURBOMACHINERY; 320201* - Energy Conservation, Consumption, & Utilization- Transportation- Air & Aerospace; 330103 - Internal Combustion Engines- Turbine; 420400 - Engineering- Heat Transfer & Fluid Flow
OSTI ID:
6806588
Country of Origin:
Japan
Language:
Japanese
Other Identifying Numbers:
Journal ID: ISSN 0578-7904; CODEN: ISHGAV
Submitting Site:
NEDO
Size:
Pages: 177-180
Announcement Date:

Journal Article:

Citation Formats

Maya, T, and Yamawaki, S. Research and development of cooled turbine for aircraft engines. Koku engine yo reikyaku turbine no kenkyu kaihatsu. Japan: N. p., 1994. Web.
Maya, T, & Yamawaki, S. Research and development of cooled turbine for aircraft engines. Koku engine yo reikyaku turbine no kenkyu kaihatsu. Japan.
Maya, T, and Yamawaki, S. 1994. "Research and development of cooled turbine for aircraft engines. Koku engine yo reikyaku turbine no kenkyu kaihatsu." Japan.
@misc{etde_6806588,
title = {Research and development of cooled turbine for aircraft engines. Koku engine yo reikyaku turbine no kenkyu kaihatsu}
author = {Maya, T, and Yamawaki, S}
abstractNote = {For the turbine which is one of the principal elements of aircraft engine, progress in turbine use material development and cooling performance further heightened for the turbine are needed to grapple with the required heightening of turbine inlet temperature. In the present paper based on the turbine inlet temperature designed to be 1600[degree]C as a target, a two-dimensional model used for the turbine cooling performance test was structurally given together with the result of the above test which aimed at confirming the design calculation. As a result of cooling design for the turbine which was about 1600[degree]C in inlet temperature, the highest gas temperature was 1890 and 1470[degree]C on the stator blade and rotor blade, respectively. Both those blades were 0.66 and 0.62, respectively in cooling efficiency. To test the cooling performance, a two-dimensional cascade was tested with a doubly amplified model of cooling blade, the use of which could set its Reynolds number near that of the actual one. As compared with the actual operation, the test was made at low temperatures of 400 to 500[degree]C and low pressures of 0.02 to 0.03MPa. The test agreed with the design calculation in result. 4 refs., 8 figs.}
journal = {Ishikawajima-Harima Giho (Ishikawajima-Harima Engineering Review); (Japan)}
volume = {34:3}
journal type = {AC}
place = {Japan}
year = {1994}
month = {May}
}