Mitsubishi Heavy Industries Limited

Mitsubishi Heavy Industries Aero Engines, Ltd.

Ryoma Nogami

Hirotaka Higashimori

Akira Fukushima

Kosuke Nishikawa

Azusa Tamugi

Hiroshi Kuma

Tsuyoshi Kitamura

Masaaki Matsuura

Kenichiro Takeishi

A ceramic matrix composite manufacturing method includes: forming a zirconia-sol containing layer that contains zirconia sol, on fabric having an interface layer formed on a periphery of each of a plurality of ceramic-made fibers; impregnating the fabric having the zirconia-sol containing layer formed, with a polymer as a precursor, to form a body; supplying oxygen to the polymer included in the body; heating the body in an inert gas atmosphere to cause a reaction of the polymer to form a matrix; and heating the body in an oxygen atmosphere to remove the interface layer, after supplying the oxygen and heating the body in the inert gas atmosphere, to generate a ceramic matrix composite in which the matrix is interposed between the fibers.

Ceramic matrix composite manufacturing method and ceramic matrix composite

A manufacturing method for a ceramic matrix composite, having a woven fabric that has multiple fiber bundles and having a matrix that is disposed in the gaps between the fiber bundles, includes: a green body formation step for forming a green body by sintering the woven fabric infiltrated with a polymer that is a precursor to the matrix; and a densification step for further infiltrating the green body with a polymer and sintering same. The densification step includes: a second infiltration step for further infiltrating the green body with a polymer so as to form an infiltrated green body; a drying step for drying the infiltrated green body so as to form a dried green body; a steam treatment step for leaving the dried green body under saturation water vapor pressure so as to form a treated green body; and a sintering step for sintering the treated green body.

Manufacturing method for ceramic matrix composite

In a centrifugal compressing apparatus, a height of a blade of an impeller is made to decrease gradually from a front edge thereof to a rear edge thereof, and a rate of change of the height of the blade is relatively large near the rear edge. The height of the blade can be made large at the rear edge side under the design restriction that an exit width of the rear edge of the blade is set to a predetermined design value. The ratio of the width of the clearance and the height of the blade is thereby made relatively large. As a result, the ratio of a flow path area occupied by a clearance flow to a flow path area occupied by a main flow is reduced. Since the pressure loss is thus made small, a drop in the efficiency can be prevented.

Centrifugal compressing apparatus

A cooled blade of a small gas turbine engine can enhance cooling performance without increasing the amount of cooling air in a simple configuration. A cooled turbine blade is provided with a cooling passagewayformed inside thereof, making the cooling air flow therein. Film-cooling holespenetrate from an inner wall surfaceto an external wall surfaceand form a cooling film. An impingement cooling memberhas a multiple number of small holesejecting the cooling air. A gap t made by the inner wall surfaceand the impingement cooling memberhas a sealing portionmounted thereon which divides the gap in a blade chord direction.

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Aichi, Japan

Ryoma Nogami