Ihi Corporation

Mitsubishi Electric Corporation

Ishikawajima-harima Heavy Industries Co., Ltd.

The Society of Japanese Aerospace Companies

Hiroshi Hamazaki

Akira Takahashi

Ruriko Yamawaki

Haruyuki Tanimitsu

Masaaki Hamabe

Ayumi Mamada

Mizuho Aotsuka

Taku Watanabe

Takayuki Yamaoka

Kunio Ooba

Katsunori Mitsuhashi

Yukie Sasaki

An engineering tool includes a display area to display a ladder program, the display area being displayed on a display screen of a display device; and a cell, which is a temporal-operator imparted region. The cell, which is a temporal-operator imparted region, is a region that is displayed in the display area and in which a temporal operator is imparted to a program module of the ladder program. The engineering tool includes a control specification editing unit and a control-specification-descriptive-expression converting unit. The control specification editing unit creates the program module. The control-specification-descriptive-expression converting unit converts the program module into a mathematical expression that can be input to a model checking program.

Engineering tool

A turbine blade has a profile including a blade suction side line, a blade pressure side line, and a blade trailing edge positioned between the rear ends of the blade suction side and pressure sidelines. The blade trailing edge of the profile is formed by connecting a pressure side arc-like curve having a constant radius of curvature and extending from the rear end of the blade pressure side line toward the camber line of the profile, and a suction side line portion which extends from the rear end of the blade suction side line toward the camber line while passing through a region closer to the camber line than a symmetric curve portion which is line-symmetric to the pressure side arc-like curve with respect to the camber line. The suction side line portion is represented by curves constituting ellipses which constitute ellipses, and a straight line.

Turbine blade

The invention includes a read-restriction setting step of setting read restriction on a program stored in hardware of an industrial product in response to a read restriction request, and a read requesting step of transmitting a read request for the program to the industrial product from an engineering tool that is a read request source. In the read-restriction setting step unique individual information retained in the hardware of the industrial product or unique individual information retained in hardware for executing an engineering tool that is a read-restriction request source is registered as registration individual information, and in the read requesting step, unique individual information retained in hardware for executing the engineering tool that is the read request source or unique individual information retained in the hardware of the industrial product is compared with the registration individual information.

Security method for engineering tools and industrial products, and security system

A turbine blade has a profile including a blade suction side line, a blade pressure side line, and a blade trailing edge formed by a curve connecting the rear ends of the blade suction side and pressure side lines to each other, wherein the curve forming the blade trailing edge of the profile is formed by connecting a pressure side curve portion which has an arc shape having a constant radius of curvature and extending from the rear end of the blade pressure side line toward the camber line of the profile, and a suction side curve portion which extends from the rear end of the blade suction side line toward the camber line while passing through a region closer to the camber line than a symmetric curve portion which is line-symmetric to the pressure side curve portion with respect to the camber line.

The invention relates to wall of a turbo machine having a cascade of blades. The wall includes: a first platform facing a first passage between blades in the cascade of blades; and a second platform facing a second passage between adjacent cascade of blades on an upstream side and cascade of blades on a downstream side, and having a circumferential outline having a distribution of radial positions. According to the invention, loss due to disturbance of flow through the gap of axially adjacent walls can be reduced.

Wall of turbo machine and turbo machine

The present invention provides a turbine blade that is exposed to a high temperature atmosphere at relatively high temperatures and to a low temperature atmosphere at relatively low temperatures, including: a concave-curve-like pressure surface that is concaved along a flow direction of fluid; a convex-curve-like suction surface that is convexed along the flow direction of the fluid; and a concave and convex formation device which causes a concave and convex portion along the flow of the fluid to appear on the suction surface when the turbine blade is exposed to the low temperature atmosphere, and which turns the suction surface into a smooth surface along a convex curve surface of the suction surface when the turbine blade is exposed to the high temperature atmosphere. With this construction, it is possible to reduce a pressure loss of the turbine blade at high Reynolds numbers in the low temperature atmosphere without increasing a pressure loss of the turbine blade at low Reynolds numbers in the high temperature atmosphere.

A blade surrounded by: a leading edge portion, which is where fluid flows in; a pressure surface which is a concave curve shape concaved along a direction the fluid flows; a suction surface which is a convex curve shape convexed along a direction the fluid flows; and a trailing edge portion, which is where the fluid flows out, in which a disturbance addition portion is provided on the suction surface closer to the leading edge portion than a maximum velocity point, where the flow velocity of the fluid is maximized on the suction surface, for disturbing a laminar flow on the suction surface and for transitioning to a turbulent flow.

Blade

A wall configuration of an axial-flow machine which can reduce the secondary flow loss is provided. A trough is formed between a blade and another blade in the blade row and extends in at least an axial direction of the blade row. The region where the trough is formed is axially between a leading edge and a trailing edge of the blade. A center line of the trough has a curvature in the same direction as a camber line of the blade. A maximum amplitude of the trough is located adjacent to an axial center of the blade or located axially between the axial center and the leading edge of the blade.

Growing community of inventors

Tokyo, Japan

Hiroshi Hamazaki