9 results about "Relative thickness" patented technology

This invention discloses a high lift-to-drag ratio, long-endurance, low-speed airfoil, revealing its maximum relative camber, maximum relative thickness, and the curve equations satisfied by its upper and lower edges. The origin of the coordinate system containing the airfoil is defined as the leading edge of the chord. The X-axis coincides with the chord line, pointing from the leading edge to the trailing edge of the airfoil. The Y-axis is perpendicular to the X-axis, pointing in the direction of the airfoil's curvature. The chord length is defined as C; therefore, the maximum relative camber is 6%C, and the maximum relative thickness is 4.5%C. The airfoil of this invention exhibits a higher lift-to-drag ratio and a higher lift coefficient while maintaining a lower drag coefficient. It reduces the weight of the wing structure, and its thin, curved shape results in a smaller internal wing cavity, optimizing aircraft weight while concentrating stress on the structure.

The application discloses a method and device for determining a blade axis position according to a wing profile thickness and a torsion angle, the method comprising: selecting a target section according to a maximum chord section of a blade; determining suction surface maximum thickness point positions and pressure surface maximum thickness point positions of a plurality of sections in a first section of the blade according to a chord distribution curve of the blade, a relative thickness distribution curve, standard wing profile maximum thickness point positions on a suction surface and a pressure surface, and a standard wing profile relative thickness, the first section being bounded by the target section and a blade tip of the blade; calculating the blade axis positions of the plurality of sections in the first section according to relative torsion angles of the plurality of sections in the first section, the suction surface maximum thickness point positions and the pressure surface maximum thickness point positions; and calculating the blade axis positions of a plurality of sections in a second section of the blade according to blade root distances of the plurality of sections in the second section, a leading edge point position of the target section and the blade root distance of the target section, the second section being bounded by the target section and a blade root of the blade.

This invention belongs to the field of steelmaking continuous casting technology, and relates to an online diagnostic method for the crystallizer of a slab continuous casting machine. The method involves inspecting and measuring the crystallizer body during the casting interval. The diagnostic criteria are as follows: the corner gap of the crystallizer copper plate ≤ 0.3mm; the absolute value of the difference between the length of one side of the inner and outer arcs of the crystallizer copper plate and the standard length of one side of the inner and outer arcs of the crystallizer copper plate ≤ 1mm; the absolute value of the relative thickness difference between the inner and outer arcs and the left and right sides of the crystallizer copper plate ≤ 3mm; the wear value of the narrow face of the crystallizer copper plate ≤ 1mm; the straightness of the crystallizer copper plate ≤ 0.5mm; within 450mm of the top edge along the length direction of the crystallizer copper plate, each crack or scratch must be ≤ 3.0mm wide, ≤ 10mm long, and ≤ 0.5mm deep, with a number of cracks or scratches ≤ 2; outside this area, each crack or scratch must be ≤ 3.0mm wide, ≤ 50mm long, and ≤ 0.5mm deep, with a number of cracks or scratches ≤ 2; and the area of ​​plating cracks at the meniscus ≤ 30×30mm. 2 If the area of ​​coating peeling off at the meniscus is 0, it meets the diagnostic criteria and is considered qualified; otherwise, it is considered unqualified.

Method (1) for the generation of a sequence of layers for a glass surface, said sequence of layers comprising, according to a layering position, layers selected from glasses, coatings, plastic interlayers, gaps with air and / or argon, opaque elements and shields or a combination thereof each having its own thickness, comprises the steps of a) providing a machine learning generative artificial intelligence algorithm based on a conversational model, said artificial intelligence algorithm being trained to generate a sequence of layers for a glass surface necessary to make a glass surface by selecting one or more layers, a relative thickness for each selected layer and a layering position; b) providing by input on a user device (10) one or more initial statements relating to a glass surface design, said initial statements comprising performance parameters required for the glass surface selected from optical, energetic, static, acoustic, usage parameters or a combination thereof; c) processing the statements provided by means of said artificial intelligence algorithm so as to generate said sequence of layers, said sequence of layers being representative of the correspondence between the statements provided and the training of the artificial intelligence algorithm, said artificial intelligence algorithm being resident in a processing unit (20) in signal communication with the user device (10), d) generating by means of said artificial intelligence algorithm a final sequence of layers representative of the correspondence between the statements provided and the training of the artificial intelligence algorithm.

The invention relates to a blade (20) for a rotor capable of rotating about an axis of rotation (AX), said blade (20) extending along a pitch axis (AXPAS) from a first end (51) to a second end (52), the blade (20) comprising a blade body (25) having a series of sections (S) substantially perpendicular to the pitch axis (AXPAS) from the first end (51) to the second end (52). The blade (20) has sections along its pitch axis with a chord that increases and then decreases, a relative thickness that decreases from an initial section (SINI) to a final section (SF), a torsional angle that continuously increases and then decreases from an initial section (SO) to the initial section (SINI), and an offset that varies with respect to the pitch axis.

The present invention relates to a blade (20) for a rotating wing that rotates about an axis of rotation (AX), said blade (20) extending along the pitch axis (AXPAS) from a first end (51) to a second end (52), the blade (20) comprising a blade body (25) having, from the first end (51) to the second end (52), a succession of sections (S) substantially perpendicular to the pitch axis (AXPAS). The blade (20) has, along its pitch axis, sections having: increasing and then decreasing chords, a relative thickness that decreases from an initial section (SINI) to a final section (SF), twist angles that increase continuously from the original section (SO) to an initial section (SINI) and then decrease, and an evolving offset with respect to the pitch axis. (Shorthand figure: Figure 2)

The application discloses a method and device for determining a blade axis position based on a main beam offset method, and the method comprises the following steps: selecting a target section according to a maximum chord length section of a blade; determining suction surface maximum thickness point positions of multiple sections in a first section of the blade according to a chord length distribution curve, a relative thickness distribution curve, suction surface maximum thickness point positions of the multiple sections in the first section, and a standard airfoil relative thickness, the first section being bounded by the target section and a blade tip of the blade; calculating front edge point positions of the multiple sections in the first section based on the suction surface maximum thickness point positions of the multiple sections in the first section and a front edge offset of the maximum thickness point positions relative to a front edge of the blade axis; obtaining the blade axis positions of the multiple sections in the first section according to the front edge point positions of the multiple sections in the first section and chord lengths of the multiple sections in the first section; and calculating the blade axis positions of multiple sections in a second section of the blade according to blade root distances of the multiple sections in the second section, a front edge point position of the target section, and a blade root distance of the target section.

The invention relates to an operating method for a rolling mill, preferably a hot rolling mill, having at least one roll stand, preferably two, three, four, five, six, seven, eight, nine or more roll stands, for shaping a metal rolling material, in particular a hot strip, by means of at least n = 2 shaping method steps in which the metal rolling material passes through a roll stand, in particular by means of at least n = 3, n = 4, n = 5, n = 6 or more shaping method steps, wherein a normalized relative thickness decrease of the (i-1)th shaping method step or of the (i-2)th shaping method step or of the (i-3)th shaping method step is less than or equal to the normalized relative thickness decrease of the ith shaping method step.

This application discloses a method and apparatus for determining the blade axis position based on airfoil geometry. The method includes: selecting a target section based on the maximum chord length section of the blade; determining the positions of the maximum thickness points of the suction surface and pressure surface of multiple sections of a first segment based on the blade's chord length distribution curve, relative thickness distribution curve, geometric data of a standard airfoil, and relative thickness of the standard airfoil, wherein the first segment is bounded by the target section and the blade tip; calculating the blade axis position of multiple sections of the first segment based on the positions of the maximum thickness points of the suction surface and pressure surface, the chord length and distance information of the multiple sections, and the blade root diameter, wherein the distance information represents the distance from the section to the blade root; and calculating the blade axis position of multiple sections of the second segment based on the blade's chord length distribution curve and blade root diameter.