Abstract: A method for payment risk control includes: receiving a request for payment graphic code generation from a mobile terminal device, the request carrying preset risk control features, the risk control features including a payment account feature of an account, a current location feature, and a station entering and exiting feature; obtaining pre-stored historical risk control features of the account according to the payment account feature in the request; detecting whether there is a transaction risk for the mobile terminal device by comparing the obtained historical risk control features with the risk control features carried in the request; and sending a risk control detection result to the mobile terminal device to generate and display a payment graphic code.

Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 4.47-4.77 inch (113.5-121.2 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 2.57-2.87 inch (65.3-72.9 mm). The airfoil element includes at least two of a first mode with a frequency of 297±10% Hz, a second mode with a frequency of 1035±10% Hz, a third mode with a frequency of 1488±10% Hz, a fourth mode with a frequency of 1524±10% Hz, a fifth mode with a frequency of 2855±10% Hz and a sixth mode with a frequency of 4462±10% Hz.

Abstract: A method for payment risk control includes: receiving a request for payment graphic code generation from a mobile terminal device, the request carrying preset risk control features, the risk control features including a payment account feature of an account, a current location feature, and a station entering and exiting feature; obtaining pre-stored historical risk control features of the account according to the payment account feature in the request; detecting whether there is a transaction risk for the mobile terminal device by comparing the obtained historical risk control features with the risk control features carried in the request; and sending a risk control detection result to the mobile terminal device to generate and display a payment graphic code.

Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 3.68-3.98 inch (93.5-101.1 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span is in a range of 1.75-2.05 inch (44.5-52.1 mm). The airfoil element includes at least two of a first mode with a frequency of 436±10% Hz, a second mode with a frequency of 1557±10% Hz, a third mode with a frequency of 1424±10% Hz, a fourth mode with a frequency of 1870±10% Hz, a fifth mode with a frequency of 3321±10% Hz and a sixth mode with a frequency of 3957±10% Hz.

Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 2.99-3.29 inch (75.9-83.6 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 1.44-1.74 inch (36.6-44.2 mm). The airfoil element includes at least two of a first mode with a frequency of 430±10% Hz, a second mode with a frequency of 1459±10% Hz, a third mode with a frequency of 2036±10% Hz, a fourth mode with a frequency of 3615±10% Hz, a fifth mode with a frequency of 4722±10% Hz and a sixth mode with a frequency of 5591±10% Hz.

Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 0.46-0.59 inch (11.8-14.9 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 0.73-0.86 inch (18.6-21.9 mm). The airfoil element includes at least two of a first mode with a frequency of 5133±15% Hz, a second mode with a frequency of 8542±15% Hz, a third mode with a frequency of 15487±15% Hz, a fourth mode with a frequency of 18774±15% Hz, a fifth mode with a frequency of 24295±15% Hz and a sixth mode with a frequency of 27084±15% Hz.

Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 4.35-4.65 inch (110.5-118.1 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 2.45-2.75 inch (62.2-69.9 mm). The airfoil element includes at least two of a first mode with a frequency of 255±10% Hz, a second mode with a frequency of 818±10% Hz, a third mode with a frequency of 1439±10% Hz, a fourth mode with a frequency of 2035±10% Hz, a fifth mode with a frequency of 3033±10% Hz and a sixth mode with a frequency of 3740±10% Hz.

Abstract: An airfoil has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 0.70-0.83 inch (17.8-21.1 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span is in a range of 0.34-0.45 inch (8.5-11.5 mm). The airfoil element includes at least three of a first mode with a frequency of 3748±15% Hz, a second mode with a frequency of 6416±15% Hz, a third mode with a frequency of 14418±15% Hz, a fourth mode with a frequency of 17417±15% Hz, a fifth mode with a frequency of 19326±15% Hz and a sixth mode with a frequency of 26648±15% Hz.

Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 2.85-3.15 inch (72.4-80.0 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 1.52-1.82 inch (38.6-46.2 mm). The airfoil element includes at least two of a first mode with a frequency of 506±10% Hz, a second mode with a frequency of 1732±10% Hz, a third mode with a frequency of 2268±10% Hz, a fourth mode with a frequency of 4007±10% Hz, a fifth mode with a frequency of 4851±10% Hz and a sixth mode with a frequency of 6416±10% Hz.

Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 3.45-3.75 inch (87.6-95.3 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 1.55-1.85 inch (39.4-47.0 mm). The airfoil element includes at least two of a first mode with a frequency of 424±10% Hz, a second mode with a frequency of 1401±10% Hz, a third mode with a frequency of 1770±10% Hz, a fourth mode with a frequency of 3336±10% Hz, a fifth mode with a frequency of 3378±10% Hz and a sixth mode with a frequency of 4141±10% Hz.

Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 17.2-18.2 inches (436-462 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span is in a range of 10.0-11.0 inches (255-281 mm). The airfoil element includes at least two of a first mode with a frequency of 51±10% Hz, a second mode with a frequency of 147±10% Hz, a third mode with a frequency of 267±10% Hz, a fourth mode with a frequency of 350±10% Hz, a fifth mode with a frequency of 454±10% Hz and a sixth mode with a frequency of 619±10% Hz.

Abstract: An airfoil including an airfoil body, a recessed portion of a first depth in a first side of the airfoil body, the recessed portion including a plurality of pockets of a second depth located within the recessed portion and ribs of the first depth located between the pockets, a cover configured to fit into the recessed portion such that an interior surface of the cover engages the ribs and an exterior surface of the cover is about flush with an exterior surface of the first side of the airfoil body, and a high energy beam weld configuration extending through the cover and into the ribs and positioned to attach the cover to the ribs.

Abstract: An airfoil including an airfoil body, a recessed portion of a first depth in a first side of the airfoil body, the recessed portion including a plurality of pockets of a second depth located within the recessed portion and ribs of the first depth located between the pockets, a cover configured to fit into the recessed portion such that an interior surface of the cover engages the ribs and an exterior surface of the cover is about flush with an exterior surface of the first side of the airfoil body, and a high energy beam weld configuration extending through the cover and into the ribs and positioned to attach the cover to the ribs.

Abstract: An assembled device for retrieving broken pieces from a root canal includes a hollow hand-held pole, a needle socket which connected to a needle cannula. An insert unit and an insert holder are inside the hollow hand-held pole. A sliding push button is outside the hollow hand-held pole which can move the insert unit up and down. The insert wedge extends to the needle cannula through the needle socket and move up and down a curved and beveled end of which engages the broken instrument and urge the broken instrument into the cutout so the device will mechanical grasp the broken instrument A cutout is spaced from the end of needle cannula. The present invention has a compact structure and stable performance. The vulnerable part can be replaced easily. It can work under the dental microscope and can also work as MTA carrier.

Abstract: The present invention provides mammalian GPR39 gene, its coded products, and the uses in regulating appetite and pain sensitivity. A pharmaceutical composition and a health product comprising GPR39 protein are also provided. The health product and the pharmaceutical composition for suppressing appetite or decreasing pain sensitivity comprise a safe and efficient amount of antagonists of mammalian GPR39 protein (for example, 0.01-99%) and a bromatologically or pharmaceutically acceptable carrier in a suitable amount (for example 1-99.99 wt %).