Patent application number | Description | Published |
20100124493 | MULTI-VANE SEGMENT DESIGN AND CASTING METHOD - Provided is an industrial gas turbine multi vane segment, which can be cast in one piece using a wax pattern method. The multi vane segment includes a platform; at least three airfoils, extending radially from the platform, having a combined airfoil volume, a chord length and an airfoil thickness; and a shroud with a shroud volume, disposed on an end of said airfoils radially distant from the platform. The ratio of the shroud volume to the combined airfoil volume defines a first ratio, while the multi vane segment has a first ratio greater or equal to 1.4:1. This ratio enables preferential solidification, during casting, of the airfoils before the shroud. | 05-20-2010 |
20110189002 | TURBINE GUIDE VANE - A turbine guide vane ( | 08-04-2011 |
20110243714 | SEALING STRUCTURE ON A SHROUD OF A TURBINE BLADE - A device on a shroud which is provided on a turbine rotor blade tip has a cutting structure designed like a line of ribs, locally projecting over the shroud radially to the rotational axis around which the turbine rotor blade is rotatably arranged. The sealing structure has a longitudinal extent (S) oriented in the direction of rotation (U) of the turbine rotor blade, tapers with increasing radial distance from the shroud, and terminates with a flat end face (St) which radially faces away from the turbine rotor blade, and can be divided into five interrelated surfaces. | 10-06-2011 |
20110286834 | GUIDE VANE FOR A GAS TURBINE - A guide vane is provided for a gas turbine and has an airfoil extending in the radial direction between an inner platform and an outer platform. The airfoil extends transversely to the direction of the hot gas flow between a leading edge and a trailing edge and has a pressure side and a suction side. A cooling slot running parallel to the trailing edge is provided on the pressure side in front of the trailing edge, a cooling medium can exit through the cooling slot from the guide vane over the entire length of the guide vane and can cool the trailing edge of the guide vane. In such a guide vane, the service life is extended by a thermal stress reducing element provided on the inner platform below the trailing edge and the cooling slot. | 11-24-2011 |
20110286849 | BLADE FOR A GAS TURBINE - A blade is disclosed for a gas turbine including an airfoil, which extends along a longitudinal axis from a blade root to a blade tip, and has a shroud segment at the blade tip. The shroud segment abuts with first and second edges against shroud segments of adjacent blades to form a ring-like shroud. The first and second edges are each provided with a respective side rail on the upper side of the shroud segment. Each of the side rails is subdivided into sections of different height and/or width. | 11-24-2011 |
20110293428 | METHOD FOR OPTIMIZING THE CONTACT SURFACES OF SHROUD SEGMENTS, WHICH ABUT AGAINST ONE ANOTHER, OF ADJACENT BLADES OF A GAS TURBINE - A method for optimizing the contact surfaces of abutting shroud segments of adjacent blades of a rotor blade row of a gas turbine includes providing a 3-D model of an individual blade. A geometry of the individual blade is calculated using the 3-D model while considering centrifugal forces, temperature stresses and pressure loads experienced in a loaded state of the blade during operation. The contact surfaces of the abutting shroud segments of adjacent blades are optimized in the loaded state of the blade. The optimization includes the surfaces of functionally serving interlocking surfaces and functionally serving wedge surfaces disposed on each side of the interlocking surfaces. A geometry of the interlocking surfaces and of the wedge surfaces in an unloaded state corresponding to the optimized contact surfaces in the loaded state of the blade is calculated. | 12-01-2011 |
20120087782 | GAS TURBINE - A gas turbine includes a rotor having a rotor groove and a rotor bore extending through the rotor, the rotor bore having a diffuser-shaped rotor bore exit. A blade is attached to the rotor and includes a blade tip having at least one dust hole. An airfoil has a leading edge and a trailing edge extending along a longitudinal axis of the blade between a lower end of the airfoil and the blade tip. A blade root is disposed at the lower end of the airfoil and is configured to be removably disposed in the rotor groove. The blade root includes a blade inlet having a cross sectional area that exceeds a cross sectional area of the rotor bore in at least one direction. A hollow blade core is disposed in the airfoil and extends along the longitudinal axis of the blade between the blade root and the blade tip. | 04-12-2012 |
Patent application number | Description | Published |
20120242988 | Linearized Variable-Dispersion Spectrometers and Related Assemblies - Wavenumber linear spectrometers are provided including an input configured to receive electromagnetic radiation from an external source; collimating optics configured to collimate the received electromagnetic radiation; a dispersive assembly including first and second diffractive gratings, wherein the first diffraction grating is configured in a first dispersive stage to receive the collimated electromagnetic radiation and wherein the dispersive assembly includes at least two dispersive stages configured to disperse the collimated input; and an imaging lens assembly configured to image the electromagnetic radiation dispersed by the at least two dispersive stages onto a linear detection array such that the variation in frequency spacing along the linear detection array is no greater than about 10%. | 09-27-2012 |
20130141695 | Optical Imaging Systems Having Input Beam Shape Control and Path Length Control - Scanning optical beam imaging systems for imaging a surface with convex curvature are provided. The systems include a sphero-telecentric objective, wherein a scanning radius of curvature of the sphero-telecentric objective is greater than an apical radius of curvature of the surface and less than or equal to four times an apical radius of curvature of the surface. | 06-06-2013 |
20130265545 | Surgical Microscopes Using Optical Coherence Tomography and Related Systems and Methods - Some embodiments of the present inventive concept provide optical coherence tomography (OCT) systems for integration with a microscope. The OCT system includes a sample arm coupled to the imaging path of a microscope. The sample arm includes an input beam zoom assembly including at least two movable lenses configured to provide shape control for an OCT signal beam; a scan assembly including at least one scanning mirror and configured for telecentric scanning of the OCT signal beam; and a beam expander configured to set the OCT signal beam diameter incident on the microscope objective. The shape control includes separable controls for numerical aperture and focal position of the imaged OCT beam. | 10-10-2013 |
20140293224 | Surgical Microscopes Using Optical Coherenece Tomography and Related Systems - Some embodiments of the present inventive concept provide optical coherence tomography (OCT) systems for integration with a microscope. The OCT system includes a sample arm coupled to the imaging path of a microscope. The sample arm includes an input beam zoom assembly including at least two movable lenses configured to provide shape control for an OCT signal beam; a scan assembly including at least one scanning mirror and configured for telecentric scanning of the OCT signal beam; and a beam expander configured to set the OCT signal beam diameter incident on the microscope objective. The shape control includes separable controls for numerical aperture and focal position of the imaged OCT beam. | 10-02-2014 |
20140313509 | Linearized Variable-Dispersion Spectrometers and Related Assemblies - Wavenumber linear spectrometers are provided including an input configured to receive electromagnetic radiation from an external source; collimating optics configured to collimate the received electromagnetic radiation; a dispersive assembly including first and second diffractive gratings, wherein the first diffraction grating is configured in a first dispersive stage to receive the collimated electromagnetic radiation and wherein the dispersive assembly includes at least two dispersive stages configured to disperse the collimated input; and an imaging lens assembly configured to image the electromagnetic radiation dispersed by the at least two dispersive stages onto a linear detection array such that the variation in frequency spacing along the linear detection array is no greater than about 10%. | 10-23-2014 |
20140354950 | Hybrid Telescope for Optical Beam Delivery and Related Systems and Methods - Optical coherence tomography (OCT) imaging systems are provided including a source of broadband optical radiation coupled to a sample arm of the OCT imaging system; a beam shaping optical assembly in the sample arm, the beam shaping optical assembly being configured to receive optical radiation from the source as a beam of optical radiation and to shape the spatial profile of the beam of optical radiation; a scan mirror assembly coupled to the beam shaping optical assembly; and objective lens assembly coupled to the beam shaping optical assembly. The beam shaping optical assembly includes a lens assembly configured to change a NA of the OCT system without changing a focus; to change a focus of the OCT system without changing a NA of the system; or to change both the NA and the focus of the OCT system responsive to a control input. | 12-04-2014 |
20150157203 | Optical Systems for Whole Eye Imaging and Biometry - Scanning optical beam imaging systems for imaging extended structures of an eye and providing biometry of an eye are provided. The systems include a focal system for shifting the focus of the scanning system from the front to the back of the eye. The systems provide for converging rays that can scan through the pupil of the eye, enabling scanning of the anterior and posterior segments of the eye using a common objective and a fixed working distance. | 06-11-2015 |