Showing papers on "Turbine blade published in 1969"
Patent•
29 Jan 1969
TL;DR: In this paper, the authors show a gas tank with a TURBINE ROTATING CHAMBER and a COMPRESSOR, COMBUSTOR, and TURBERINE SEQUENTIALLY ARRANGED.
Abstract: THE DISCLOSURE SHOWS A GAS TURBINE ENGINE HAVING A COMPRESSOR, COMBUSTOR, AND TURBINE SEQUENTIALLY ARRANGED. A ROTATING, AIR ENTRY CHAMBER IS FORMED AT THE BASE OF THE TANGS OF TURBINE BUCKETS, WHICH PROJECT FROM THE TURBINE ROTOR INTO THE HOT GAS STREAM FROM TEH COMBUSTOR. A RELATIVELY STATIONARY, ANNULAR NOZZLE FORMS THE ENTRANCE TO THIS ROTATING CHAMBER. AIR IS DUCTED FROM THE DISCHARGE OF THE COMPRESSOR TO THIS NOZZLE. THE NOZZLE IS PROVIDED WITH VANES WHICH ACCELERATE THE COMPRESSOR DISCHARGE AIR INTO THE ROTATING CHAMBER WHICH IS AT A LOWER PRESSURE. THE NOZZLE IMPARTS, TO THE COOLING AIR, A VELOCITY VECTOR HAVING A COMPONENT RELATIVE TO THE ROTATING CHAMBER (AND TURBINE ROTOR), WHICH IS GENERALLY AXIAL. THE AIR IS REDUCED IN STATIC TEMPERATURE, AS IT IS ACCELERATED THROUGH THE NOZZLE, AND ENERGY LOSSES ARE MINIMIZED DUE TO THE VELOCITY VECTOR OF THE COOLING AIR BEING ESSENTIALLY AXIAL RELATIVE TO OPENINGS IN THE TURBINE ROTOR, WHICH THE AIR ENTERS TO FLOW THROUGH PASSAGEWAYS PROVIDING AN INTERNAL COOLING MECHANISM FOR THE TURBINE BUCKETS.
39 citations
Patent•
Avco1
TL;DR: In this paper, a TURBINE BLADE is described as a core consisting of a core having open troughs closed by a laminated skin to provide COOLANT flow through the skin.
Abstract: A TURBINE BLADE IS COMPRISED OF A CORE HAVING OPEN TROUGHS ENCLOSED BY A LAMINATED SKIN TO FORM COOLANT PASSAGES. EACH LAYER OF THE LAMINATED SKIN HAS COOPERATING CAVITIES WHICH PROVIDE COOLANT FLOW PASSAGE THROUGH THE SKIN. THIS RESULTS IN THE COMBINATION OF CONVECTION COOLING WITHIN THE MULTI-LAYERED LAMINATED SKIN, AND BOUNDARY LAYER COOLING ON THE SURFACE OF THE TURBINE BLADE.
38 citations
Patent•
23 Dec 1969TL;DR: In this article, the authors proposed a cutaway portion of the wall of the cavity, which allowed the cooling fluid to discharge into a main gas stream through the turbine at the area of lowest pressure on the blade surfaces.
Abstract: A cooled turbine blade for gas turbines and the like having passageways for conducting a relatively cool fluid through the blade to its tip and incorporating a walled cavity at the tip of the blade. The wall of the cavity has a cutaway portion which permits the cooling fluid to discharge into a main gas stream through the turbine at the area of lowest pressure on the blade surfaces. This permits the flow of fluid from the discharge orifices of the passageways to be more uniform from the leading to the trailing edge of the blade and reduces the required gas pressure on the entire cooling system.
36 citations
Patent•
Avco1
TL;DR: In this paper, the authors discuss the use of bundling pins or inserts into the HOLES WHICH are forMED in the TURBINE BLADES DURING CASTING.
Abstract: THIS DISCLOSURE RELATES TO TURBINE BLADES AND THE METHOD FOR BONDING PINS OR INSERTS INTO THE HOLES WHICH ARE FORMED IN THE TURBINE BLADES DURING CASTING.
33 citations
TL;DR: In this article, a non-contact method for measuring the vibrations of the turbine blades of a turbine while in motion is proposed, which is clearly preferable to one involving transducers (such as strain gauges coupled to slip-rings or miniature transmitters).
Abstract: A RELIABLE method of measuring the vibrations of the blades of a turbine while in motion is needed1. A non-contact method is clearly preferable to one involving transducers (such as strain gauges coupled to slip-rings or miniature transmitters). We have been investigating the possibility of using a laser Doppler system for such a measurement.
33 citations
Patent•
21 Nov 1969TL;DR: An electrode device for electrolytically forming the blades of multi-stage turbine rotors is described in this paper, where a tubular, inwardly and outwardly insulated shank and a generally annular electrode food are mounted on the shank.
Abstract: An electrode device for electrolytically forming the blades of multi-stage turbine rotors as integral portions of the rotor body comprises a tubular, inwardly and outwardly insulated shank and a generally annular electrode food mounted on the shank and having an inner contour in accordance with the profile of a turbine blade to be formed The outer contour of the electrode foot is made wider than corresponds to the arcuate blade division of the rotor to be produced so that the electrolytical operations for forming each two adjacent turbine blades overlap between the two blades The working face of the electrode foot is curved cylindrically in accordance with the blade-foot circle of the rotor to be produced The inner edge of the annular electrode foot is rounded in accordance with the rounding desired at each blade for where the blade meets the foot circle The tool electrode affords the complete removal of workpiece material from between the resulting blades and also produces an undistorted cylindrical area along the foot circle between adjacent blades
24 citations
Patent•
Avco1
TL;DR: In this paper, a hollow turbine blade is filled with a liquid metal which is cooled by means of a plurality of tubes through which coolant air is passed, the walls of the turbine blade are in contact with the liquid metal, the air acting as the system coolant.
Abstract: A hollow turbine blade is filled with a liquid metal which is cooled by means of a plurality of tubes through which coolant air is passed. The walls of the turbine blade are in contact with the liquid metal which acts as the heat exchange mechanism, the air acting as the system coolant.
24 citations
Patent•
13 Nov 1969
TL;DR: In this article, a method for manufacturing a turbine blade in which a sheet metal strip, corresponding in its dimensions to the developed blade, is provided with cooling passages, thereafter a thinner metal strip is attached to the sheet metal strips provided with the grooves by welding or brazing to form a blade wall, and thereafter the blade wall is placed about a tool core and is deformed into the shape of the blade whereupon the ends of the strips are connected with each other by welding to form the trailing edge of the turbine blade.
Abstract: A method for manufacturing a turbine blade in which a sheet metal strip, corresponding in its dimensions to the developed blade, is provided with cooling passages, thereafter a thinner sheet metal strip is attached to the sheet metal strip provided with the grooves by welding or brazing to form a blade wall, and thereafter the blade wall is placed about a tool core and is deformed into the shape of the blade whereupon the ends of the strips are connected with each other by brazing or welding to form the trailing edge of the blade.
24 citations
01 Oct 1969
TL;DR: Crack initiation prediction in high temperature components subjected to arbitrary thermal- mechanical cycling has been studied in this article, where the authors propose a method to predict the crack initiation in a high temperature component subjected to thermal mechanical cycling.
Abstract: Crack initiation prediction in high temperature components subjected to arbitrary thermal- mechanical cycling
21 citations
Patent•
14 Nov 1969
TL;DR: A bladed wheel, fan, turbine, or the like is mounted in or below the downdraft side of the carburetor and has an even number of equidistantly spaced blades alternate ones of which are tilted at a relatively large angle to the axis of the turbine to cause rotation of turbine by the fuel intake suction while the remaining blades each of which is positioned between two propulsion blades have any angle of tilt with respect to the tilt angle of the propulsion blades such that said remaining blades resist and slow down the speed of rotation of a turbine while causing more thorough
Abstract: A bladed wheel, fan, turbine or the like is mounted in or below the downdraft side of the carburetor and has an even number of equidistantly spaced blades alternate ones of which are tilted at a relatively large angle to the axis of the turbine to cause rotation of the turbine by the fuel intake suction while the remaining blades each of which is positioned between two propulsion blades have any angle of tilt with respect to the tilt angle of the propulsion blades such that said remaining blades resist and slow down the speed of rotation of the turbine while causing more thorough mixing of the fuel and air mixture, consequent to increased vaporization of the fuel.
17 citations
Patent•
18 Aug 1969
TL;DR: In this paper, a rotary device is used to rotate the hub of a turbine and the blades of the turbine for testing the turbine, and the indicator means are used to indicate the attainment of the governed speed when the turbine is driven by the device and the power delivered by the rotor is increased beyond that which the turbine can absorb.
Abstract: Apparatus including in combination a turbine (1), a governor, a rotary device (11) and indicator means (14). The governor is adapted to govern the speed of the turbine by varying the pitch of the turbine blades (2) between their low-pitch position and their high-pitch position. The rotary device is connectable to rotate the hub of the turbine and thereby the blades, for testing the turbine, and the indicator means are adapted to indicate the attainment of the governed speed when the turbine is driven by the device and the power delivered by the device is increased beyond that which the turbine can absorb with the blades in the low-pitch position.
Patent•
05 Nov 1969TL;DR: In this article, a pre-guide lattice or guide fin arrangement for discharging into the turbine blades and in addition in accordance with a feature of the construction, the discharge section immediately after the turbine blade is provided with a retarding after-guide-lattice for guiding the fuel discharged by the turbine into the main combustion chamber and also for adding an additional fuel component, either fuel or oxidizer, at such location.
Abstract: A liquid fuel rocket engine construction includes the usual main combustion chamber having a nozzle discharge. One or more precombustion chambers are arranged ahead of the main combustion chamber in a position to discharge combustion gases generated therein through turbine blades of an auxiliary turbine arranged directly adjacent the rear end of the main combustion chamber. The auxiliary turbine drives at least two separate fuel component pumps, one of which discharges first through the walls of the main combustion chamber for cooling purposes and then into a precombustion chamber, and the other of which discharges only partially into the precombustion chamber and then into the discharge from the auxiliary turbine and into the main combustion chamber. The precombustion chamber is operated either with excess fuel or oxidizer. The construction includes a preguide lattice or guide fin arrangement for discharging into the turbine blades and in addition in accordance with a feature of the construction, the discharge section immediately after the turbine blades is provided with a retarding afterguide lattice for guiding the fuel discharged by the turbine into the main combustion chamber and also for adding an additional fuel component, either fuel or oxidizer, at such location. In a preferred form, the trailing ends of the afterguide lattice are provided with nozzle discharge openings for facilitating the discharge of the fuel component into the main combustion chamber at such location.
Patent•
23 Oct 1969TL;DR: A HOLLOW TURBINE BLADE with a CIRCUMFERENTIAL SHROUD SEGMENT at its outer end is described in this paper, where it is shown how to construct an arched construction for maximal strength.
Abstract: A HOLLOW TURBINE BLADE IS PROVIDED WITH A CIRCUMFERENTIAL SHROUD SEGMENT AT ITS OUTER END. A CIRCUMFERENTIAL PLENUM DIRECTS COOLING FLUID FROM THE BLADE TO HOLES WHICH EXTEND TO THE INNER SURFACE OF THE SHROUD SEGMENT TO PROVIDE FOR COOLING OF THE SHROUD. THE PLENUM IS OF ARCHED CONSTRUCTION FOR MAXIMUM STRENGTH.
TL;DR: In this paper, a cascade test was performed to investigate the nature of flow in the rotor blade channels of axial flow turbines with partial admission, and the results showed that the tangential force on the cascade increases with the Reynolds number within the range ( 0·82 × 10 5 to 1·38 × 105 ) covered by the experiments.
Patent•
14 Mar 1969TL;DR: In this article, a jig and gaging fixture is used to determine acceptable and nonacceptable turbine blades, particularly nozzle vanes, and precision positioning of the same between a pair of concentric shrouds in a single operation.
Abstract: A jig and gaging fixture providing determination of acceptable and nonacceptable turbine blades, particularly nozzle vanes, and precision positioning of the same between a pair of concentric shrouds in a single operation.
Patent•
31 Dec 1969TL;DR: In this article, an arrangement for installing and subsequent locking of side-entry blades in a turbine rotor disc is provided for allowing radial entry of the last blade into the rotor or disc without distortion of any of the blades.
Abstract: An arrangement is provided for installing and subsequent locking of side-entry blades in a turbine rotor disc. Heretofore, the placement of the last blade in a circular row of turbine blades has required twisting, bending and distorting of the last and adjacent blade at assembly because of interference between adjacent blades. This jeopardized their reliability in service. The present arrangement permits radial entry of the last blade into the rotor or disc without distortion of any of the blades.
01 Feb 1969
01 Sep 1969
TL;DR: In this article, the authors describe the equipment and techniques for an investigation into the mechanisms which deposit sub-micron particles on turbine blades, with particular reference to the deposition of fog within the low-pressure steam turbine.
Abstract: The equipment and techniques for an investigation into the mechanisms which deposit sub-micron particles on to turbine blades are described, with particular reference to the deposition of fog within the low-pressure steam turbine. The experimental studies were centred around a cascade of blades in an open-circuit low-speed wind tunnel. Deposition on the blades of small solid uranine particles entrained in the main air flow was detected and measured using the fluorescent properties of the particles. Some results from preliminary deposition tests are given.
01 Jun 1969
01 Oct 1969
TL;DR: In this article, Bayley and Turner have shown that by the combination of high heat transfer coefficients within the interstices of the porous material, and a reduction in heat transfer rate by injection into the boundary layer on the hot-gas side of the blade, effective cooling rates can be achieved.
Abstract: If maximum gas temperatures aire to rise appreciably above 1500°K, the value currently achieved in advanced aero-engines, alternatives to the present internal convective methods of air-cooling the first-stage turbine blades will have to be sought. One of the most promising developments lies in the use of porous blade materials, through which cooling air can be “effused” or “transpired”. In a recent paper Bayley and Turner have shown that by the combination of high heat transfer coefficients within the interstices of the porous material, and a reduction in heat transfer rate by injection into the boundary layer on the hot-gas side of the blade, effective cooling rates can be achieved.
Patent•
27 Mar 1969TL;DR: High toughness steel suitable for the manufacture of turbine blades is composed of defined quantities of Cr, Ni, Co, Mo, and iron, wherein the molybdenum may be replaced by tungsten as discussed by the authors.
Abstract: High toughness steel suitable for the manufacture of turbine blades is composed of defined quantities of Cr, Ni, Co, Mo, and iron, wherein the molybdenum may be replaced by tungsten. The steel composition also contains minor amounts of carbon, silicon and manganese. The composition of this steel is selected so that the quantity of delta Ferrite and the Ms point have predetermined values. The steel is subjected to heat treatment, cooling and aging.
Patent•
[...]
TL;DR: In this paper, an improved TURBINE BLADE is used to support a LOAD-CARRYING STRUT with a CURVED LEADING EDGE PORTION and a TRAILING Egressor.
Abstract: AN IMPROVED TRANSPIRATION COOLED TURBINE BLADE COMPRISING A SHEATH OF PERMEABLE MATERIAL SURROUNDING A LOAD-CARRYING STRUT, THE ASSEMBLY HAVING A GENERALLY AIRFOIL CONFIGURATION WITH A CONCAVE AND CONVEX SURFACE JOINED BY A CURVED LEADING EDGE PORTION AND A TRAILING EDGE PORTION. THE STRUT IS PROVIDED WITH LANDS AND GROOVES WITH A LAND PORTION EXTENDING INTO ABUTMENT AGAINST THE SHEATH TO THEREBY REINFORCE THE SHEATH AGAINST IMPACTION OF GAS ENTRAINED PARTICLES. THE LAND PORTION IS OFFSET FROM AN IMAGINARY LONGITUDINAL PLANE CONTAINING THE CHAMBER LINE IN A DIRECTION AWAY FROM THE CONCAVE SURFACE OF THE BLADE SO THAT COOLING FLUID CAN BLEED THROUGH THE SHEATH AT THE LEADING EDGE PORTION ON BOTH SIDES OF THE IMAGINARY LONGITUDINAL PLANE.
01 Jan 1969
TL;DR: In this paper, the first phase of a two-phase, two-year program that involves the design and testing of a single-stage, high-work radial inflow turbine is described.
Abstract: : The report describes the work accomplished in the first phase of a two-phase, two-year program that involves the design and testing of a single- stage, high-work radial inflow turbine. This turbine will be typical of one required for advanced gas turbine engines employing high cycle pressure ratios and high turbine inlet temperatures. The objectives of Phase I were to establish a preliminary turbine design, to confirm the preliminary design through cold-flow tests, and to conduct a fabrication study. The Phase I final preliminary turbine design is the result of iterative aerodynamic-structural- heat transfer analyses. The final selections of number of nozzle vanes, number of rotor blades and rotor cooling air ejection method were confirmed and supported by cold-flow tests. The fabrication study showed some material property problems which require additional investigation.
01 Nov 1969
TL;DR: Tangential jet, tandem, jet flap and vortex generator blade concepts investigated for turbine blade loading efficiency as discussed by the authors, and the results showed that turbine blade load loading efficiency can be improved.
Abstract: Tangential jet, tandem, jet flap and vortex generator blade concepts investigated for turbine blade loading efficiency
01 Jun 1969
TL;DR: Stator setting effect on single stage turbine performance, considering blade loss and surface velocity distribution, is discussed in this article, where the authors consider a single-stage turbine with a single blade.
Abstract: Stator setting effect on single stage turbine performance, considering blade loss and surface velocity distribution
01 Sep 1969
TL;DR: In this article, the results of intrascope observations and instrument traverses in the final stages of three large steam turbines and describes the processes controlling the distribution of erosion on the moving blades.
Abstract: The paper presents the results of intrascope observations and instrument traverses in the final stages of three large steam turbines and describes the processes controlling the distribution of erosion on the moving blades. Concentrations of eroding water are shown to be produced by complex steam flows in the final stage which redistribute the water depositing on the surfaces of fixed blades. Of the three turbines considered, each has a different redistribution process, two leading to concentrated erosion, the third to a more uniform distribution of damage. In the former two turbines, it was found that the concentrations of water could be dispersed by small fences fitted to the fixed blade trailing edge, this simple modification promising to extend significantly the operating life of the moving blades.
Patent•
02 Apr 1969
TL;DR: A double-beam C.R.E. display is used in this paper to measure turbine blades, where the position of the shaft, blade root, and blade tip can be detected.
Abstract: 1,147,737. Electro-physical measurement; turbine blade vibration. I.E. ZABLOTSKY, J.A. KOROSTELEV and L.B. SVIBLOV. Jan. 8, 1968, No.1095/68. Heading G1N. Apparatus for measuring vibrations of turbine blades, utilizing a double-beam C.R.T. display comprises five sensors 3, 4, 5, 26, 28 arranged as shown Fig. 1 to detect the position of the shaft, blade root, and blade tip. The shaft sensor 3 synchronizes the vertical sweep generator 10 for the lower beam and the horizontal sweep generator 12 for the upper beam; sensor 5 controls the "brightener" for both beams; sensors 14, 26, 28 may be selectively switched to control the horizontal scan of the lower beam and a scan-ratecounter 21. The following measurements may be made: - Amplitude of blade-tip oscillation is indicated by the length of the trace such as 33 with sensor 14 switched in i. e. tip and root measurements. Velocity of oscillation of the blade tip is indicated by the position of the spot or trace from the beginning of the scan line with sensor 26 switched in. The length of the trace is proportional to the difference between the maximum and minimum velocities. Angle of twist is indicated by the position of the spot along a scan line with sensor 28 switched in. A trace instead of a spot indicates the presence and amplitude of Torsional Oscillations. Speed of rotation is shown by the number of spots 34 produced by the upper beam. The position of the root of the blade is conveniently indicated by marks (14') on a disc attached to the shaft Fig.2 (not shown).