Abstract: A method of determining fuse parameters in a reciprocating gas compressor ensures a safe failure upon exceeding an overload limit. Stresses and bolted joint behavior for critical components in compressor running gear are evaluated using a finite element analysis. Capabilities of the critical components during an overload event are evaluated using a propagation and variances tool. The capabilities of the critical components are compared against overload conditions. At least one of an optimal fuse location and a fuse geometry are determined according to the comparison to establish a safe failure point upon exceeding the overload limit. With a mechanical fuse defining a failure point, critical compressor components can be protected from damage, and personnel can be protected from risk of a gas leakage.

Abstract: Variable nozzle (10) for a gas turbine fixed to a shaft (11) equipped with a pressurized upper surface (12) and a depressurized lower surface (14) opposite to the upper surface (12), the variable nozzle comprises a series of substantially “C”-shaped sections, each having a first rounded end (20) and a second rounded end (21), each section of the series of sections also having the concavity facing upwards with respect to a base (90) and arranged one after another continuously, in the direction of an axis of the shaft (11) along a curved line (60), the at least second degree curved line (60) lies on a surface (70) having an axis orthogonal to the axis of the shaft (11) and also tilted with respect to the base (90) by an angle (80).

Abstract: A rapidly replaceable non-return device (110) for a petrochemical refinery reactor (112), of the type comprising: a support tube (114), connected to a portion of the reactor (112), this support tube (114) being provided internally with a cartridge (116) containing a ball (118), the cartridge (116) having, around an inlet hole (121) for a processed fluid, a seat (122) for housing the ball (118), and having slots (120) for the outflow of the said processed fluid; the cartridge (116) is fitted removably in the support tube (114).

Abstract: Assembly system (10) for a thermocouple (16) for a gas turbine equipped with a supporting element (12) in which the thermocouple (16) is housed, the supporting element (12) has a series of holes (45) for the inlet of the discharge gases of the gas turbine and a cavity (50) in which they are mixed before flowing through an opening (14) of the supporting element (12).

Abstract: The present invention relates to a method for treating organs subject to erosion by liquids, in particular vapour turbine components, which contemplates laser plating with a cobalt-based alloy comprising chromium from 28 to 32% by weight; tungsten from 5 to 7% by weight; silicon from 0.1 to 2% by weight; carbon from 1.2 to 1.7% by weight; nickel from 0.5 to 3% by weight; iron from 0.01 to 1% by weight; manganese from 0.01 to 1% by weight; molybdenum from 0.2 to 1% by weight; possible impurities or other elements from 0 to 0.5% by weight and cobalt the complement to 100%.

Abstract: In order to limit the flame temperature peaks following sudden load variations, corresponding control is planned of the position of the blades (13) of the distributor with variable geometry, of a single-shaft gas turbine (18); in particular, the control system proposed comprises a direct-action regulator (21) consisting of a calculation unit (22), which implements the simplified running model of the gas turbine (18), and a feedback regulator (20), which makes it possible to recuperate any inaccuracies of the direct-action regulator (21), caused by variations of the performance of the turbine (18), relative to those planned by the model, or caused by modelling errors.

Abstract: The present invention relates to a cobalt-based alloy for the coating of organs subject to erosion by liquid comprising chromium 28–32% by weight, tungsten 6–8% by weight, silicon 0.1–2% by weight, carbon 1.2–1.7% by weight, nickel 3–6% by weight, molybdenum 1–3%, cobalt the complement to 100%. The invention also relates to an application method of the alloy on organs subject to erosion by liquid, in particular vapour turbine blades, to reduce the metal erosion rate following impact with liquids.

Abstract: The present invention relates to a method for treating organs subject to erosion by liquids, in particular vapour turbine components, which contemplates laser plating with a cobalt-based alloy comprising chromium from 28 to 32% by weight; tungsten from 5 to 7% by weight; silicon from 0.1 to 2% by weight; carbon from 1.2 to 1.7% by weight; nickel from 0.5 to 3% by weight; iron from 0.01 to 1% by weight; manganese from 0.01 to 1% by weight; molybdenum from 0.2 to 1% by weight; possible impurities or other elements from 0 to 0.5% by weight and cobalt the complement to 100%.

Abstract: System for connecting and locking blades which are fixed circumferentially to a rotor disc (1) of an axial compressor, comprising a plurality of blades (10, 10?) positioned in an array along the circumference of rotor disc (1), each blade (10, 10?) being provided with a shaped root (13) for connection to the rotor disc (1), and a dowel for positioning and locking the blades (10, 10?) in a predetermined position in a circumferential seat (3) which has a shaped profile and which is formed along the circumference of the rotor disc (1). At least one insertion slot (4) intersects the circumferential seat (3) to permit the insertion of the roots (13) of the blades (10, 10?) and the dowel.

Abstract: A centrifugal compressor for high pressure (10) with improved efficiency, of the type comprising a rotor (12), an inner case (14), diffusers (16) and diaphragms (18), wherein the surfaces which are subjected to passage of the flow of gas have been subjected to burnishing working.

Abstract: A sealing system (10) which ensures the safe operation of very high pressure centrifugal compressors which process lethal gases. The system comprises sealing means (18, 19) separated by an annular chamber (12), and a discharge line (32) for collecting and eliminating any gases that may be released.

Abstract: An improved flame tube or “liner” (112) for a combustion chamber (110) of a gas turbine with low emission of pollutants, of the type comprising a cylindrical structure connected to the outlet of a premixing chamber (114) by means of a truncated conical end (120), in which the premixing chamber (114) is supplied with air which is guided by a cavity (116) which is located between the flame tube (112) and outer walls (118) of the combustion chamber (110), this air circulating in the opposite direction to the flow of combustion products; a first cylindrical region (122) of the flame tube (112) is surrounded by a cylindrical casing (136) which creates an annular chamber (138).

Abstract: A system (10) for sealing and pressurization for the support cushion (24) of a gas turbine (20), wherein the gas turbine (20) is provided with a compressor (21), with which there is associated an inner barrel (23), and the support cushion (24) is in turn provided with seals (38, 39) relative to the axis of the compressor (21), and has at least one pipe (33) for the venting discharge. The air is fed into the inner barrel (23), using the venting piping (33) of the support cushion (24), such as to create a flow of air, which starts from an intermediate stage of the compressor (21), and goes towards the inner barrel (23).

Abstract: A device (10) for circulating sealing gas for mechanical dry seals (11) of a centrifugal compressor (13) at times when the machine is stationary and pressurized; the device comprises a sealed reciprocating compressor (12), which includes a piston (14) slidable in a cylinder (16), and the piston (14) is moved by a magnetic coupling to an external magnetic element (20) which moves along the said cylinder (16).

Abstract: A system to feed cooling air to a gas turbine, wherein the cooling air is taken from a high-pressure source, inside the gas turgine, and is conveyed to radial accelerators (129, which give rise to the tangential acceleration of the air in the direction of the peripheral motion of the rotor surface. After it has been accelerated to the peripheral sepped of the rotor, the cooling air enters radial holes (13), and, whilst passing radially through the radial holes (13), undergoes a reduction in the quantity of tangential motion, Subsequently, the cooling air is released into the hollow rotor, with a correspondingly reduced outlet radius (14). A series of labyrinth seals combined with brush seals separate the chamber for combined with brush seals separate the chamber for feeding of air to the radial holes (13), from the low-pressure environment around the pad #2 (15) of the said gas turbine.

Abstract: A sealing device for connection of a pipe in a hole, wherein the fitting is free, with play, of the type comprising pressure means to thrust the pipe in the direction of the hole, and a washer with an annular shape, with a central hole into which the pipe is inserted and secured; this washer has a base which is shaped according to a spherical annular surface portion and is disposed with this spherical base facing the hole, the spherical base being thrust against the hole by these pressure means.

Abstract: A system for connecting a low-pressure jet to a transition duct in a gas turbine, in which the said low-pressure jets are arranged in sectors of two or three stator blades and are filled on to the ring of the jets. The platforms of the jets are provided with a channel inside which the transition duct is positioned by means of an edge. Furthermore, centering between the transition duct and the ring of the jets is achieved directly using centering means at three or more points.

Abstract: A device (10) for circulating sealing gas for mechanical dry seals (11) of a centrifugal compressor (13) at times when the machine is stationary and pressurized; the device comprises a sealed reciprocating compressor (12), which includes a piston (14) slidable in a cylinder (16), and the piston (14) is moved by a magnetic coupling to an external magnetic element (20) which moves along the said cylinder (16).

Abstract: An easy-fit heat screening device (110) for connecting a cooling pipe (112) and a through-hole (114) formed in a nozzle support ring (116) of a gas turbine, of the type comprising a tubular structure (118) which has an external diameter smaller than a diameter of the through-hole (114) and into which the cooling pipe (112) extends; this tubular structure (118) has at the top a shaped annular end (126) which is inserted inside a groove (130) formed in the through-hole (114).

Abstract: A tube plate for tube bundles for chemical reactors and heat exchangers in general, includes a plurality of components, with shapes that are complementary to one another, in order to form a complete plate. The components may be produced separately, and are connected to one another subsequently by means of mechanical joints, in order to form the tube plate. The components which form the tube plate are joined to one another by of a plurality of pins, or other mechanical connections, which are inserted in corresponding holes provided in the respective components. This joint can be completed by means of welded connections on the mechanical connection parts.