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UnitedStatesPatent0 " 1 3,378,229 Patented Apr. 16, 1968 2 3,378,229 RADIAL FLOW TURBINE John R. Erwin, Cincinnati, Ohio, assignor to General Electric Company, a corporation of New York FiledJuly16,1965,Ser.No.472,486 14 Claims. (Cl. 253-74) The present invention relates to a radial ?ow machine, and, more particularly, to a radial out?ow turbine that produces high work output in a single stage. dimensional radial only flow is provided to ensure maxi mum recovery of the kinetic energy in the discharged gases. Brie?y stated, the invention provided a radial out?ow turbinethatmay beasingleordualentryturbineand which has a rotor disc mounted on a shaft for rotation. A second disc concentric with and axially spaced from the rotor disc is provided. Arranged serially outward then there are provided cam'bered turbine buckets preferably 10 ofconstantuntwistedcross-sectionwhichjointhediscs together to provide a single rotatable unit with an un obstructed curved inlet gas passage to direct gas radially outward through nozzles and between the discs which rotate in one direction only. The location of the turbine One of the problems in small lightweight jet type en gines is the inability to provide a satisfactory turbine that obtainssufficientlyhighwork outputand isstilsmalland lightweight enough to be satisfactory for many applica tions.Allmulti~stageaxialturbines,althoughcapable15 bucketsatasufficientradialdistancefromthecenterof of reasonable performance because of very light bucket loadings,areprohibitivelyexpensiveformany engineap plications. This is true because of the many rows of high precisionbucketsofcostlymaterialsrequiredtoobtainthe work needed. Additionally, axial flow single stage super~ sonic turbines as well as centrifugal turbines of conven tional geometry (whether in?ow or out?ow) have failed to develop the level of efficiency required to make a high performance engine. Their performance limitations are related to the basic axial inlet aerodynamics which gen erate strong spanwise variations in ?uid velocity and ?ow angle into each bucket row. These spanwise variations of ?uid properties creating secondary ?ows not only restrict the attainable performance of the turbine but require com rotation and the unobstructed inlet ensure that only radial or two-dimensional gasflow reaches the turbine buckets. The discs extend radially beyond the turbine buckets to form a rotating vaneless diffuser passage which is followed byavanedstationarydiffuser.A scrollcollectingmeans is radially spaced from the diffuser passage to collect the gas from the vaned diffuser for distribution. Modi?cation permits a vaneless diffuser chamber or passage between the end of the rotating diffuser and the vaned diffuser as well as a freely rotatable separate diffuser beyond the rotor.Further,modi?cationpermitsboundarylayerbleed to be used when necessary. Whilethespecificationconcludeswithclaimsparticular ly pointing out and distinctly claiming the subject matter plextwistedandtaperedbladeshapesthatareexpensive 30 whichisregardedastheinvention,itisbelievedthein to manufacture. Additionally, the non-uniform ?ow leav ing the buckets prevents efficient recovery of the kinetic energyofthedischarginggas. A largecontributiontorotorlossesinaxialandcen trifugal ?uid machines such as turbines is believed to be due to relative vorticity. Turbines of the conventional radial in?ow impeller type, which receive the gas in a radial direction and direct it axially outward operate with a secondary ?ow superimposed on the free stream through ?ow relative velocity. Although the inlet absolute vorticity may be zero, the relative vorticity sets up a circulatory ?ow in a plane normal to the through?ow velocity with in the con?nes of the rotating passage. This results in a secondary velocity which analysis has shown is of the same order of magnitude as the through?ow velocity and con tributes signi?cantly to rotor, diffuser and stator losses. The main object of the present invention is to provide a radial out?ow ?uid machine as applied to a turbine which is so constructed as to substantially eliminate sec ondary velocity and thus prevent any effect on the main free stream through?ow velocity. Another object is to provide such a turbine in which the construction and location of the turbine buckets is such ‘that the ?ow is substantially two-dimensional throughout the complete turbine and the rotational speed of any spanwise element of a rotor bucket is substan tiallyconstant. A furtherobjectistoprovidesuchaturbineinwhich the gas is handled only in a radial out?owing direction and boundary layers are centrifuged outward in the tur bine. Another object is to provide such a turbine which uti lizes a rotating diffuser in combination with turbine buck ets accepting only radially directed gas either su'bsonical 1y or supersonically, to provide a very high work output singlestagemachine. A furtherobjectistoprovisesuchaturbineinwhich the sealing problems are reduced to a minimum and the vention will be better understood from the following description taken in connection with the accompanying drawingsinwhich: FIGURE 1isapartialcross-sectionalviewofatypical single inlet turbine of the instant invention; FIGURE 2isapartialcross-sectionalviewshowingthe nozzle,bucketandvanelayoutofFIGURE 1; FIGURE 3 is a view similar to FIGURE 1 showing adualentryturbine; FIGURE 4 is a partial cross-sectional view showing thenozzle,bucketandvanelayoutofFIGURE 3; FIGURE 5isapartialcross-sectionalviewofatypical turbinelikeFIGURE 1ofamodi?edformemployinga freely rotating vaned diffuser; FIGURE 6isapartialcross-sectionalviewofatypical single entry turbine in a modi?ed form; and FIGURE 7 is a partial sectional view of a modi?ed form offreelyrotatingdiffuserstructure. ' In ?uid machines such as conventional radial in?ow turbines having radial entrance for gas and radial buck ets, secondary vortical ?ows are created. When the tur bine wheel rotates, the incoming gas, which is given a high tangential velocity by nozzles, enters radially into the passage between the buckets. The motion of this gas relative to the stationary elements is a free vortex. The incoming gas, as a vortex, is then turned within the buck ets toward the axial direction. This additional turn into the axial direction sets up an even further or secondary vortex due to the difference in tangential bucket velocities between hub and tip. The secondary vortex generates ad ditional energy absorbing circulatory ?ows within the pas sages of the rotor creating undesirable frictional losses and non-uniform ?ow. Also, the secondary vorticity repre sents energy which cannot be recovered in the form of pressure. The performance of the vaned or vaneless dif fusers following the rotor is very sensitive to the uni formity of the flow which is received from such rotor. High efficiency in both rotor and diffuser is obtained by sealingstructureismaintainedonasmalldiameterofthe 70 producingandmaintainingtwo-dimensionalorradialonly rotor. ?ow. Another object is to provide a turbine in which two AIn co-pending application, Ser. No. 243,561 ?led Dec.PDF Image | ERWIN RADIAL FLOW TURBINE
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