Patent US4165949A successfully refreshed from Google Patents.
US4165949A
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High efficiency split flow turbine for compressible fluids
Assignee: GROUPE EUROPEEN POUR LA TECHNIQUE DES TURBINES A VAPEUR GETT
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Filing: 1977-08-04
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Granted: 1979-08-28
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Expires: 1997-08-04
Abstract
Abstract In a turbine for a compressible fluid in which the fluid flow leaving the tepenultimate stage is separated into two coaxial flows, the inner flow passes through both the penultimate and the final stages of the turbine while the outer flow passes through the final stage only. This high efficiency arrangement for the last stages of a high power turbine exploits the advantages made available by using titanium as the blade material.
Inventors
- 👤 Gilbert Riollet
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-08 07:09
CPC Classifications
H; H01; H01J; H01J23/00; H01J23/02; H01J23/06; H01J23/065; F; F01; F01D; F01D1/00; F01D1/02; F01D1/023; F01D1/16; F01D5/00; F01D5/12; F01D5/14; F01D5/141; F01D5/142; H01J23/08; H01J23/083; H01J23/087; H01J23/0876; H01J23/16; H01J23/24; H01J23/26; H01J23/30; H01J23/36; H01J23/40; H01J23/42; H01J23/48; H01J23/50; H01J25/00; H01J25/34; H01J25/36; H01J25/38; H01P; H01P5/00; H01P5/08; H01Q; H01Q11/00; H01Q11/02; H01Q11/08; H03; H03C; H03C3/00; H03C3/30; H03H; H03H2/00; H03H2/005; H03H2/006; H04; H04M; H04M19/00; H04M19/02; H04M5/00; H04M5/04; H04Q; H04Q3/00; F05; F05D; F05D2200/00; F05D2200/20; F05D2200/21; F05D2200/211; Y; Y02; Y02D; Y02D30/00; Y02D30/70; Y10; Y10S; Y10S415/00; Y10S415/914
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
236 words
A multistage axial flow turbine for compressible fluids in which the fluid leaving the antepenultimate stage is separated into coaxial radially inner and radially outer flows which are subject to substantially the same decrease in enthalpy between the outlet from the antepenultimate stage and the outlet of the turbine, the inner flow passing through the penultimate and final stages with respective decreases in enthalpy of h 1 and h 2 and the outer flow passing through only the final stage, the rotor blades of the last stage including a wall serving as a barrier between the inner flow and the outer flow, the rotor blades of the last stage having a discontinuity in variation in profile from root to tip with the profile of the blade radially outward of the wall between the two flows being more highly curved than that radially inward of said wall, and the degree of reaction of said rotor blades at this barrier when operating under optimum conditions having a value x 2 on the outer flow side which is substantially equal to x 1 ·h 2 /(h 2 +h 1 ) where x 1 is the value of the degree of reaction on the inner flow side such that the pressure on the radially outward side of the wall is maintained substantially equal to the pressure on the radially inward side of the wall across said last stage rotor blades.
Claim 2
Dependent Claim
236 words
A multistage axial flow turbine for compressible fluids in which the fluid leaving the antepenultimate stage is separated into coaxial radially inner and radially outer flows which are subject to substantially the same decrease in enthalpy between the outlet from the antepenultimate stage and the outlet of the turbine, the inner flow passing through the penultimate and final stages with respective decreases in enthalpy of h 1 and h 2 and the outer flow passing through only the final stage, the rotor blades of the last stage including a wall serving as a barrier between the inner flow and the outer flow, the rotor blades of the last stage having a discontinuity in variation in profile from root to tip with the profile of the blade radially outward of the wall between the two flows being more highly curved than that radially inward of said wall, and the degree of reaction of said rotor blades at this barrier when operating under optimum conditions having a value x 2 on the outer flow side which is substantially equal to x 1 ·h 2 /(h 2 +h 1 ) where x 1 is the value of the degree of reaction on the inner flow side such that the pressure on the radially outward side of the wall is maintained substantially equal to the pressure on the radially inward side of the wall across said last stage rotor blades.
Claim 3
Dependent Claim
21 words
A turbine for compressible fluids according to claim 1, wherein x 2 is between 0.3 and 0.7 times x 1 .
Claim 4
Dependent Claim
21 words
A turbine for compressible fluids according to claim 1 wherein the rotor blades of the final stage are made of titanium.
Claim 5
Dependent Claim
76 words
A turbine for compressible fluids according to claim 1, wherein the wall separating the coaxial inner and outer flows in the rotor of the final stage being at a mean distance r p from the turbine axis which is substantially equal to ##EQU3## where r b is the distance of the blade roots from the turbine axis and x 0 is the degree of reaction at the base of the inner flow in the final stage.
Claim 6
Dependent Claim
62 words
A turbine for compressible fluids according to claim 4 wherein the wall between the coaxial inner and outer flows in the rotor of the final stage is at a mean distance r p from the turbine axis and r p is between 1.25 and 1.55 times r b where r b is the distance of the blade roots from the turbine axis.
Claim 7
Dependent Claim
40 words
A turbine for compressible fluids according to claim 1, wherein the decrease of enthalpy of the inner flow as it passes through the penultimate stage is substantially equal to the decrease of enthalpy as it flows through the final stage.
Claim 8
Dependent Claim
19 words
A turbine for compressible fluids according to claim 6, wherein x 2 is substantially equal to x 1 /2.
Claim 9
Dependent Claim
82 words
A turbine for compressible fluids according to claim 6, wherein the wall between the coaxial inner and outer flows in the rotor of the final stage is at a mean distance r p from the turbine axis which is substantially equal to r b ·√2·(1-x 0 )/(1-x 2 ), where r b is the distance of the blade roots from the turbine axis and x 0 is the degree of reaction at the base of the inner flow in the final stage.
Claim 10
Dependent Claim
59 words
A turbine for compressible fluids according to claim 6, wherein the wall between the coaxial inner and outer flows in the rotor of the final stage is at a mean distance r p from the turbine axis which is substantially equal to r b ·√2, where r b is the distance of the blade roots from the turbine axis.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1982-08-27 | 1983-02-26 | 1983-08-28 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1986-08-27 | 1987-02-26 | 1987-08-28 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1990-08-27 | 1991-02-26 | 1991-08-28 | $7700.00 | Window Closed / Lapsed |