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1l with inner and outer radii and supplying high-tem perature elastic ?uid, means creating a radial temperature gradient in said ?ow passage wherein the temperature is higher to ward the outer radius of said ?ow passage, 5 a plurality of radially extending nozzle partitions dis posed at the end of said ?ow passage and imparting varying tangential velocity components to the motive ?uid at diiferent radii, so that the tangential Mach numbers of said velocity components vary inversely 10 withtheradius,and a plurality of radially extending rotatable blades dis posed beyond said nozzle partitions, said blades hav ing entry angles varying with radius to conform to the ?uid leaving said nozzle partitions when the 15 blades are rotating. 3. In an axial flow turbine, means de?ning a ?ow passage of arcuate cross-section with inner and outer radii and supplying high-tem perature elastic ?uid, 20 means creating a radial temperature gradient in said ?ow passage, wherein the temperature is higher to ward the outer radius of the ?ow passage, a plurality of radially extending nozzle partitions dis posed at the end of the ?ow passage and imparting 25 varying tangential velocity components to the motive ?uid at different radii, so that the tangential Mach numbers of said velocity components vary inversely with the radius, and a plurality of radially extending rotatable turbine 30 buckets disposed beyond said nozzle partitions, said buckets having varying entry angles at different radii to conform to the ?ow of motive ?uid leaving the nozzle partitions when the buckets are rotating, said buckets becoming thicker and having a gross cross sectional area which increases with increasing radius. 4. In an axial ?ow turbine, means de?ning a ?ow passage of arcuate cross-section with inner and outer radii and supplying high-tem 40 perature elastic ?uid, means creating a radial temperature gradient in said ?ow passage, comprising a radially directed jet of lower temperature ?uid introduced from the inner radius of said ?ow passage, 12 temperaturesT correspondingtothoseradii,accord ing to the expression where VUR and TR are tangential velocity compo nent and static temperature respectively at 2.refer ence radius rR, and a plurality of radially extending rotatable blades dis posed beyond said nozzle partitions, said blades hav ing entry angles varying with radius to conform to the ?uid leaving said nozzle partitions when the blades are rotating. 6. In an axial ?ow turbine, means de?ning a ?ow passage of arcuate cross-section with inner and outer radii, and supplying high-tem perature elastic ?uid, means creating a radial temperature gradient in said ?ow passage, wherein the temperature is higher to ward the outer radius of the ?ow passage, a plurality of radially extending nozzle partitions dis posed at the end of said ?ow passage and impart ing varying tangential velocity components to the elastic ?uid at different radii, so that the tangential Mach numbers of said velocity components vary in versely with the radius, and plurality of radially extending rotatable turbine buck~ ets disposed beyond and conforming to the ?uid ?ow leaving said nozzle partitions, each of said buckets having a gross cross-sectional area exposed to the elastic ?uid which increases with increasing radius, and also de?ning a recess in the outer portion there of, whereby the radial centrifugal stress on said buckets decreases rapidly at ?rst near the root and then decreases less rapidly near the tip, the radial centrifugal stress distribution in said buckets be ing selected to substantially approximate the allow able stress/temperature curve for the bucket ma terial over the range of temperature in said ?ow passage. 7. A turbine bucket having a vane portion with a root and a tip, and designed for operation in an elastic ?uid whose temperature is substantially greater at the vane tip than at the vane root, said vane portion being posed at the end of said ?ow passage and imparting varying tangential velocity components to the elastic ?uid at different radii, so that the tangential Mach numbers of said velocity components vary inversely withtheradius,and from root to tip and de?ning a recess in the outer por tion thereof which increases in size from a midportion of the vane to the tip so that the vane has a net cross sectional area which ?rst increases and then decreases 50 withradius,wherebytheactualcentrifugalstressonthe vane decreases more rapidly with increase in radius near the root and then less rapidly with increase in radius near the tip, said vane being fabricated from a material in which the allowable stress decreases rapidly with in 3,135,496 apluralityofradiallyextendingnozzlepartitionsdis 45 constructedsoastoincreaseingrosscross-sectionalarea a plurality of radially extending rotatable turbine buckets disposed beyond said nozzle partitions and having varying entry angles at different radii to con form to the ?ow of elastic ?uid leaving said nozzle partitions,whenthebucketsarerotating,saidbuckets 55 crease in temperature at a lower temperature and then having a gross cross-sectional area as seen by the elastic ?uid which increases with radius, said buckets also de?ning hollowed-out recesses in the outer por tions thereof, whereby the net cross-sectional area of the bucket ?rst increases and then decreases with in creasingradius. 5. In an axial ?ow turbine, means de?ning a ?ow passage of arcuate cross-sec tionwithinnerandouterradiiandsupplyinghigh 65 temperature elastic?uid, means creating a radial temperature gradient in said ?ow passage, wherein the stagnation temperature is higher toward the outer radius of said ?ow passage, and less rapidly with increase in temperature at a higher tem perature, the change in net cross-sectional area of the vane being selected so that the changing rate of decrease in centrifugal stress on the vane approximates the chang ing rate of decrease in allowable stress of the material over a temperature range corresponding to the range of vane temperatures from root to tip. 8. In an axial ?ow turbine for operation with motive ?uid having a substantial radial temperature gradient, apluralityofstationarynozzlepartitionshavingra dially inner roots and radially outer tips, said noz zle partitions de?ning ?uid exit angles which vary gradually from root to tip so as to direct the ?uid leaving the tips in a more tangential direction than the ?uid leaving the roots, and a plurality of rotating buckets receiving motive ?uid from said nozzle partitions, said buckets hav ing radially inner roots and radially outer tips and de?ning bucket entry angles which vary gradually from root to tip in a manner such that the bucket a plurality of radially extending nozzle partitions dis posed at the end of said ?ow passage and impart ing varying tangential velocity components VU to the elastic ?uid at diiferent radii r at the gas static 75 70PDF Image | FLOW TURBINE WITH RADIAL TEMPERATURE GRADIENT
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