Mitsubishi Heavy Industries Aero Engines, Ltd.

Yasuyuki Uetsuki

Tadayuki Hanada

Takafumi Ota

Yohei Fujimoto

Tomoyuki Onishi

Eiichi Yanagisawa

Ryutaro Fujisawa

Yusuke Ichihashi

An aircraft component is used for an aircraft gas-turbine engine. The aircraft component includes an annular part, a flange, and a boss. The annular part has an outer circumferential surface. The flange is formed at one end portion of the annular part in an axial direction. The boss projects from the outer circumferential surface of the annular part to the radial direction. On a section cut along an axial direction of the annular part, the outer circumferential surface of the annular part between the flange and the boss has a taper part that is formed into a tapered shape in which plate thickness becomes thicker from the flange toward the boss.

Aircraft component and aircraft gas-turbine engine

The present invention enables machining to be easily performed and reduces stress concentration on a machined hole that is formed in a cylindrical member. Recesses () recessed in the depth direction of a machined hole () are formed on circumferential side-portions of the machined holeformed in a cylindrical member (). In each of the recesses (), a part of the opening edge is formed to be a circular arc portion () that has a circular arc shape, the bottom is formed to be gradually shallowed by an inclined surface () toward an opened portion () in which the circular arc shape is opened, from a part along the circular arc portion (), and the circular arc portion () is disposed toward the machined hole ().

Stress reduction structure, gas turbine casing, and gas turbine

An aircraft component is used in a gas turbine engine for an aircraft. The aircraft component includes an annular part having an outer peripheral surface, and a boss part protruding from the outer peripheral surface of the annular part in a radial direction. In the boss part, at least two through-holes are formed to penetrate the boss part in the radial direction at predetermined intervals. In the boss part around the two through-holes, a cut-out part where a part of the boss part is cut out is formed.

Aircraft component and gas turbine engine for aircraft

Included in a gas turbine casing and a gas turbine are a first casing that has a first flange portion, first connecting holes, and first notches; a second casing that has a second flange portion, a plurality of second connecting holes, and second notches; and fastening bolts to fasten the first flange portion and the second flange portion with the portions being closely attached to each other and with each fastening bolt penetrating the corresponding first and second connecting holes. A first radial direction ratio (L/H) is set to be from 0.09 to 0.11 where H is a length of each of the first flange portion and the second flange portion in a radial direction, and L is a length of each of the first notch and the second notch in a radial direction.

Growing community of inventors

Tokyo, Japan

Yasuyuki Uetsuki