Abstract: Computer system and method for determining frequencies of various components of a volume choke volume dampener to be attached to a compressor. The method includes determining a sound spectrum of a cavity of the compressor without attaching the dampener to the compressor; calculating an acoustic wavelength of the cavity; receiving a length of a proximal nozzle of the dampener; and calculating, based on the acoustic wavelength of the cavity and the length of the proximal nozzle of the dampener, multiple order frequencies associated with the proximal nozzle of the dampener and the cavity of the compressor, wherein the proximal nozzle of the dampener is proximal to the cavity of the compressor when the dampener is attached to the compressor.

Abstract: A blade is mountable to a disc. The blade comprises a blade platform and a blade root extending from the blade platform. The blade root comprises a first hook and a second hook, a first neck between the first hook and the blade platform, and a second neck between the first hook and the second hook. Each hook comprises a contact surface and a non-contact surface. An angle between each contact surface and each non-contact surface is optimized to reduce local stresses.

Abstract: A blade mountable to a disc comprises a blade platform and a blade root extending from the blade platform. The blade root comprises first, second, and third hooks and first, second and third necks. Each hook comprises a contact surface and a non-contact surface, and an angle between each contact surface and each non-contact surface is optimized to reduce local and average stresses.

Abstract: A rotating blade for a steam turbine includes a root section and an airfoil section contiguous with the root section. The airfoil section is shaped to optimize aerodynamic performance while providing optimized flow distribution and minimal centrifugal and bending stresses. The blade also includes a tip section continuous with the airfoil section, and a cover formed as part of the tip section. The cover defines a radial seal that serves to minimize tip losses. The rotating blade is capable of running at operating speeds between 5626 and 11250 rotations per minute.

Abstract: A rotating blade for a steam turbine includes a root section and an airfoil section contiguous with the root section. The airfoil section is shaped to optimize aerodynamic performance while providing optimized flow distribution and minimal centrifugal and bending stresses. The blade also includes a tip section continuous with the airfoil section, and a cover formed as part of the tip section. The cover defines a radial seal that serves to minimize tip losses. The rotating blade is capable of running at operating speeds between 5626 and 11250 rotations per minute.

Abstract: A rotating blade for a steam turbine includes a root section and an airfoil section contiguous with the root section. The airfoil section is shaped to optimize aerodynamic performance while providing optimized flow distribution and minimal centrifugal and bending stresses. The blade also includes a tip section continuous with the airfoil section, and a cover formed as part of the tip section. The cover defines a radial seal that serves to minimize tip losses. The rotating blade is capable of running at operating speeds between 5626 and 11250 rotations per minute.

Abstract: A rotating blade for a steam turbine includes a root section and an airfoil section contiguous with the root section. The airfoil section is shaped to optimize aerodynamic performance while providing optimized flow distribution and minimal centrifugal and bending stresses. The blade also includes a tip section continuous with the airfoil section, and a cover formed as part of the tip section. The cover defines a radial seal that serves to minimize tip losses. The rotating blade is capable of running at operating speeds between 5626 and 11250 rotations per minute.

Abstract: Mechanical overloads in a reciprocating gas compressor can cause irreparable damage to compressor components if the source of the overloads is not repaired. A method of detecting mechanical overloads includes applying an overload indicator across an interface between components in the compressor, and observing a mechanical condition of the overload indicator. The mechanical condition of the overload indicator is indicative of whether the compressor experienced a mechanical overload. By placing the indicator in an appropriate location in the compressor, overload conditions can be checked during routine inspections and maintenance checks.

Abstract: System for controlling and optimizing the emissions of a catalytic combustor in a single-shaft gas turbine (10), comprising at least one calculation unit for implementing a mathematical model of the operation of the said gas turbine (10), on the basis of a set of predetermined parameters, by means of which the aforesaid emissions can be optimized during variations of the operating conditions of the turbine over a range of external environmental conditions from approximately ?29° C. to +49° C.

Abstract: Disk of a disk rotor for a gas turbine comprising a central portion (22), an intermediate portion (24), an outer portion (28), a series of axial pass-through holes (27) for a series of tie rods and a series of slots (50) for housing a corresponding series of vanes, the central portion (22) comprises a central axial pass-through hole (23), a first collar (30) situated at a first end and a second collar (40) situated at a second end of the central portion (22). The series of holes (27) is positioned in the outer portion (28) of the disk so as to obtain high dynamic characteristics of the rotor and at the same time a sufficient useful life thereof.

Abstract: System for monitoring a reciprocating compressor, comprising a unit for measuring parameters relating to the operating state of the compressor, a processing unit for comparing the values of these measured parameters with critical values contained in a database associated with the said processing unit. This processing unit sends a signal determined by a match between the measured values and the critical values; this signal represents an anomaly in the operating state of the compressor.

Abstract: A method for controlling the useful life of gas turbines of a production plant includes a) creating a succession of gas generator groups of gas turbines to be subjected to maintenance, b) substituting a first gas generator group of gas turbines of the succession with an auxiliary gas generator group, c) inspecting the first substituted gas generator group of gas turbines, d) substituting a second gas generator group of gas turbines of the succession with the first verified gas generator group of gas turbines, e) inspecting the second substituted gas generator group of gas turbines, and f) repeating steps b), c) d) and e) for all the gas generator groups of gas turbines of the succession.

Abstract: A control method for a gas turbine engine is described. The control method includes, for example, corrected control parameters which are adjusted for environmental and/or operating parameters. Control of a fuel valve and a bleed valve in the gas turbine are described relative to various control algorithms.

Abstract: Combustion system (10) for a gas turbine equipped with a premixing chamber (12) for air which is mixed with the fuel injected from a series of holes (11) creating a main central flame which is formed in a flame tube (14), the premixing chamber (12) is convergent towards a connection end with a combustion chamber comprising the flame tube (14), the combustion system (10) comprises a series of pilot devices (20) with premixing of the fuel gas, which create a series of corresponding pilot flames suitable for stabilizing the main central flame itself, at the same time reducing the polluting emissions.

Abstract: A mounting system for a liner within a combination chamber of a gas turbine, where the liner is secured at one upstream end to a burner and at an opposite downstream end to a transition duct, the mounting system comprising: a first elastic head comprised of a first ring-shaped housing having first and second pluralities of radially spaced, axially extending teeth, with a first annular groove between said first and second pluralities of teeth, wherein said first elastic head is secured to said upstream end of said liner, with an end portion of said liner received within said first annular groove; and a second elastic head comprised of a second ring-shaped housing having third and fourth pluralities of radially-spaced, axially-extending teeth, with a second annular groove between said third and fourth pluralities of teeth, wherein said second elastic head is secured to said downstream end of said liner, with an opposite end portion of said liner received within said second annular groove.

Abstract: A connection between a rod and crosshead in a reciprocating compressor includes threaded units, an anti-rotational securing device and axial positioning elements, wherein the threaded units has a first inner lock nut, provided with an inner thread onto which there is screwed a threaded end portion of the rod and provided with two outer threads with a different diameter, one of which is for connection to the left-handed anti-rotational securing device, and the units also include a second outer lock nut in the inner diameter of which a thread is provided.

Abstract: A vane system for a centrifugal compressor (10), comprising two rows (15, 20) of vanes (15?, 20?) installed in series inside a suction duct (14), the first row (15) of fixed vanes (15?) being suitable for homogenizing the gas flow that passes through them and sending it to the second row (20) of adjustable vanes (20?) equipped with a guiding mechanism comprising a mechanical system (30) suitable for varying the orientation of the vanes (20?).

Abstract: Multistage centrifugal compressor having a horizontally openable tank, comprising a lower semi-tank and an upper semi-tank, a shaft having a series of rotors and a series of stages each of which comprising, in turn, a series of lower semi-diaphragms and a series of upper semi-diaphragms, a lower half-ring and an upper half-ring which can be coupled to form a bearing ring, the lower half-ring being fastened internally to the lower semi-tank , and the corresponding upper half-ring being fastened to the upper semi-tank , in each stage of the multistage centrifugal compressor, the lower semi-diaphragms are rigidly constrained to one another to form a first pile of lower semi-diaphragms and, the corresponding upper semi-diaphragms are rigidly constrained to one another to form a second pile of lower semi-diaphragms, the first pile can be constrained to the lower half-ring and the second pile can be constrained to the upper half-ring.

Abstract: Multistage centrifugal compressor includes at least one stage which, in turn, has a lower half-tank, an upper half-tank, a series of lower half-diaphragms, a shaft equipped with a series of rotors, a series of upper half-diaphragms, a lower suction half-diaphragm, an upper suction half-diaphragm, the lower suction half-diaphragm and the upper suction half-diaphragm include a lower portion (71) and an upper portion (72), respectively, suitable for being coupled with the lower half-diaphragms and with the upper half-diaphragms, respectively, to form a first pile of lower half-diaphragms and a second pile of upper half-diaphragms, respectively.

Abstract: Mechanical overloads in a reciprocating gas compressor can cause irreparable damage to compressor components if the source of the overloads is not repaired. A method of detecting mechanical overloads includes forming a mechanical fuse that is configured to strain under overload conditions, and observing a condition of the mechanical fuse. The condition of the mechanical fuse is indicative of whether the compressor experienced a mechanical overload. By simply observing the mechanical fuse, overload conditions can be checked during routine inspections and maintenance checks.