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3 10, 1962 and assigned to the same assignee as the instant invention, there is disclosed and claimed a compressor de sign that bypasses the vorticity problem by providing sub stantially two-dimensional ?ow in combination with a rotating vaneless diffuser for high pressure ratios at high e?iciency. 4 (over 30") of the rotor buckets 16 provides high strength and high work output at moderate rotational speed (less than 1500 feet per second). This provides higher work extraction at a given rotational speed as compared to a ‘conventional turbine. The turbine described is next serially provided with a rotating diffuser in combination with the two-dimensional flow by extending discs 10 and 12 radially beyond the pe riphery of buckets 16 to form a rotating preferably slight 3,878,229 -The present invention is directed to a similar combina tion of elements to form an efficient high work output turbine. The individual elements per so are known and the improvementintheinstantinventionliesintheuseofa 1O lyexpandingvanelessdiffuserpassage17.Asinanydif vaned rotating diffuser in combination with substantially two-dimensionalflowbyparticularlydesigningandlocat ing and combining the turbine buckets and other means serially as will be pointed out. Thus, with the instant in vention, very high work output is obtainable by a single rowofrotatingbucketsinadditiontootheradvantagesof boundary layer control and sealing as will be apparent as the description proceeds. fusing ?ow passage, boundary layer ?uid becomes a prob lem and the present invention has a built-in boundary layer control by providing diffuser passage 17 with rotat ing walls. It can be seen that by rotation of diffuser pas sage 17, the rotating side walls of the discs 10 and 12 ener gize the boundary layer due to the centrifugal ?eld on any particle, since al boundary layer particles will have a high tangential velocity approaching or equal to the rotational velocity of the rotor discs. The vaneless rotating diffuser passage 17 which diffuses the ?ow from a relative number of about 1.5 down to about 1.0 (theabsolutevelocitythroughthediffuserbeingsubsonic) is followed by a vaned diffuser 18 radially spaced from the diffuser passage 17 for further diffusion and resulting pres sure rise of the gas from the rotor. Of course vanes 18 may be constructed in two rows to perform their func tion in two steps. As well known, any suitable collecting means such as scroll 19 may be employed to carry the exhaust gas to a discharge by connecting itto the vaned Referring?rsttoFIGURE 1,theinventionisshown in a typical single entry radial out?ow modi?cation. This comprises a rotor disc 10 rotatable around a central axis orshaft11whichcarriesthedisc.A seconddiscorhoop 12 is provided concentric with and axially spaced from rot-or disc 10 and also spaced radially from shaft 11 to de?ne, with the rotor disc 10, an unobstructed curved in let gas passage 13 between the discs to direct gas radially outward between the discs. The term “unobstructed” means, as shown, that there is nothing between the ?uid entering, such as gas, and the disc surface so that there isradialonlyentryof?uidintotheturbinenozzlesand 30 diffuser.Sincethereisasigni?cantstaticpressureriseac then into the rotating system before any tangential ve locity is imparted to the ?uid. In order to provide the proper swirl to the incoming gas radial strut supported turbine nozzles 14 are provided at a distance fro-m the center of rotation and radially upstream of the rotor buck ets as shown to ensure that they receive only radially?ow ing gas thus ensuring two-dimensional flow through the passage between the discs and eliminating the undesirable secondary vorticity and consequent losses. Turbine nozzles 14 are preferably given a curature for turning the incom ing radial gas in the direction of rotor or disc rotation to give the gas a tangential velocity as seen in FIGURE 2. The nozzles inject high velocity gas into the rotor. High work otuput with high e?iciency results. For efficient 01" design operation turbine nozzles 14 can be made adjust able by pivoting about axis 15 in any suitable manner not shown. complished between the leading edge of the vaned dif fuser 18 and the collecting means 19 a boundary layer problem may be encountered. If so, control may be ob tained by suitable boundary layer suction or blowing means 20 as shown in the walls of the vaned diffuser or the walls may be porous surfaces, these means of bound ary layer control being well known. As shown in FIGURE 2, off-design operation may re— quire variable turbine nozzles and the outlet or vaned dif fuser vanes 18 may also be made variable or adjustable in the same manner. A stationary wall vaneless diffuser may thereby follow vanes 18 before the collector 19 if desired. With the construction just described, sealing problems are also minimized. The whole rotating structure is sur rounded by closely spaced casing 21 ‘and sealing means 22 are provided at a small radius on each disc between the disc and casing well inwardly of the disc outer pe riphery. This puts the seal at a lower rotational speed of 'One of the difficulties of turbines of any type is the presence of boundary layers in the flow passages. The presentinventionprovidesabuilt-inboundarylayercon-, therotorcomparedtothatoftherotorperiphery.Be trol by means of a rotating diffuser in con-junction with the two-dimensional ?ow through the turbine. The gas is turned through a large angle by means of a single stage of turbine buckets 16 which are highly cambered as shown in FIGURES 2 and 4 and are secured to the discs 10 and ‘12 so that the discs and buckets rotate as a unit in one direction only and in the opposite direction of camber of thebucketsasshownbythearrowinFIGURE 2.Itisto be noted that the buckets 16 are particularly located at a radial distance from the center of rotation so that they 60 receive substantially radial ?owing gas only so the flow is twoedimentional, thus reducing the losses. Because of the radial two-dimensional ?ow, buckets 16 are of constant camber untwisted cross-section resulting in inexpensive manufacturing costs. It is to be noted also that bucket-s :16 are so arranged that their leading edges are constant cause of the rotation of the gas in the spaces between 1-2 and 21 and between 10 and 21, the pressure increases out wardly, and the pressure gradient across the seal 22 is lessened. With this construction, no sealing is required at the periphery of the disc between rotating diffuser passage 17 and vaned diffuser 18 because the small sealed volume between casing 21 and the discs, once charged with ?uid, is an effective seal itsef for the gas ?owing through the turbine. The radial velocity of the gas is controlled by pref erably contacting of the passage through the rotor buck ets. The radial velocity of the gas may be decreased through the rotating diffuser if desired as shown in FIG URE 1.Becauseoftheincreaseintheradialdistance,the diffuser portion of the passage may be constant or ex panded in width to decrease the radial velocity. The actual expansion depends on the ability of the diffuser portion of the passage to maintain the ?ow without separation from the disc Walls. The boundary layer particles have a in the spanwise direction or parallel to the center of ro tation. The result is that the rotational speed of any span wise cross-section is constant. This is desirable because the total pressure relative to the rotor remains constant 70 high tangential velocity (equal to the rotor speed) that across the span of the blades and the ability to extract work from the gas flow through the turbine is constant because the rotational speed of any radial point on the bucket is constant. The passage through the buckets may expand, contract or be straight as shown. The high camber is much greater than the absolute tangential velocity of the gas stream leaving the rotor buckets. A very strong [boundary layer control effect isproduced on the boundary layer ?uid due to centrifugal forces, so the rotating dif fuser walls can sustain a high static pressure rise.PDF Image | ERWIN RADIAL FLOW TURBINE
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