US3765791A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Turbine nozzle support
Assignee: MTU Aero Engines AG
•
Filing: 1971-11-08
•
Granted: 1973-10-16
•
Expires: 1991-11-08
Abstract
Abstract A mounting support of a turbine nozzle, especially of a turbine guide-vane ring connected to a hot gas scroll in the end section of a turbo assembly, which is axially elastically connected at this end section to another adjacent assembly by way of a plugtype connection; the guide-vane ring is thereby rigidly connected at its inner shroud with a housing of the turbo assembly whereas it is axially movably held with its outer shroud in a collar of the gas duct which is itself supported at the adjacent assembly; the outer shroud thereby forms together with an annular piston a structural unit whose end surface facing upstream is acted upon by the gas pressure prevailing upstream of the guide-vane ring whereas its end surface facing downstream is acted upon in part by a high compressor end-pressure and in part by the pressure prevailing downstream of the turbine.
Inventors
- 👤 K Trappmann
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-03 08:52
CPC Classifications
F; F01; F01D; F01D9/00; F01D9/02; F01D9/04; F01D9/042
Claims Analysis
Total Claims: 23
Claim 1
Independent Claim
314 words
An arrangement for supporting turbine guide vane means in position on a turbo-assembly between a gas duct and a rotatable turbine unit of said turbo assembly such that said guide vane means guides the flow of gases from said gas duct to said turbine unit, wherein said guide vane means includes a plurality of guide vane blades rigidly connected to and supported between inner and outer guide vane rings; said arrangement comprising: relatively fixed housing means, first connecting means rigidly connecting one of said inner and outer guide vane rings to said housing means, collar means on said gas duct, second connecting means interposed between the other of said inner and outer guide vane rings and said collar means for supporting said other of said inner and outer guide vane rings at said collar means, said second connecting means including piston means axially fixed to said other of said inner and outer guide vane rings and axially movably supported in said collar means, said piston means having respective upstream and downstream facing end surfaces with respect to gas flow through said turbo-assembly, said upstream facing end surface being acted upon by the gas pressure prevailing immediately upstream of said guide vane means, at least a portion of said downstream facing end surface being acted upon by the gas pressure prevailing immediatley downstream of said turbine unit, and high pressure communicating means for communicating high pressure gas under a pressure higher than the pressure prevailing immediately downstream of said turbine unit directly with at least a portion of said downstream facing end surface, whereby said high pressure gas and the gas pressure prevailing immediately downstream of said turbine unit counteracts at least a part of the bending forces on the guide vane means resulting from movement of said piston means due to pressure forces on said upstream facing end surface during operation of said turbo-assembly.
Claim 2
Dependent Claim
314 words
An arrangement for supporting turbine guide vane means in position on a turbo-assembly between a gas duct and a rotatable turbine unit of said turbo assembly such that said guide vane means guides the flow of gases from said gas duct to said turbine unit, wherein said guide vane means includes a plurality of guide vane blades rigidly connected to and supported between inner and outer guide vane rings; said arrangement comprising: relatively fixed housing means, first connecting means rigidly connecting one of said inner and outer guide vane rings to said housing means, collar means on said gas duct, second connecting means interposed between the other of said inner and outer guide vane rings and said collar means for supporting said other of said inner and outer guide vane rings at said collar means, said second connecting means including piston means axially fixed to said other of said inner and outer guide vane rings and axially movably supported in said collar means, said piston means having respective upstream and downstream facing end surfaces with respect to gas flow through said turbo-assembly, said upstream facing end surface being acted upon by the gas pressure prevailing immediately upstream of said guide vane means, at least a portion of said downstream facing end surface being acted upon by the gas pressure prevailing immediatley downstream of said turbine unit, and high pressure communicating means for communicating high pressure gas under a pressure higher than the pressure prevailing immediately downstream of said turbine unit directly with at least a portion of said downstream facing end surface, whereby said high pressure gas and the gas pressure prevailing immediately downstream of said turbine unit counteracts at least a part of the bending forces on the guide vane means resulting from movement of said piston means due to pressure forces on said upstream facing end surface during operation of said turbo-assembly.
Claim 3
Dependent Claim
40 words
An arrangement according to claim 1, wherein said first connecting means rigidly connects said inner guide vane ring to said housing means, and wherein said second connecting means is interposed between said outer guide vane ring and said collar means.
Claim 4
Dependent Claim
36 words
An arrangement according to claim 1, wherein said high pressure communicating means includes means for conducting said high pressure gas from a high pressure compressor of said turbo-assembly which is arranged downstream of said turbine unit.
Claim 5
Dependent Claim
36 words
An arrangement according to claim 2, wherein said high pressure communicating means includes means for conducting said high pressure gas from a high pressure compressor of said turbo-assembly which is arranged downstream of said turbine unit.
Claim 6
Dependent Claim
29 words
An arrangement According to claim 1, further comprising seal means for sealing the high gas pressure with respect to the gas pressure prevailing immediately downstream of said turbine unit.
Claim 7
Dependent Claim
29 words
An arrangement according to claim 2, further comprising seal means for sealing the high gas pressure with respect to the gas pressure prevailing immediately downstream of said turbine unit.
Claim 8
Dependent Claim
27 words
An arrangement according to claim 2, wherein said outer guide vane ring includes a radially outwardly extending protrusion which engages with radial play in said piston means.
Claim 9
Dependent Claim
38 words
An arrangement according to claim 1, wherein a portion of said turbo-assembly including said gas duct and guide vane means is axially yieldingly connected with an adjacent portion of said turbo-assembly by way of a plug-type connecting means.
Claim 10
Dependent Claim
32 words
An arrangement according to claim 8, wherein said plug-type connecting means includes an extension on said piston means which axially and yieldingly engages in a corresponding opening of said next adjacent portion.
Claim 11
Dependent Claim
38 words
An arrangement according to claim 2, wherein a portion of said turbo-assembly including said gas duct and guide vane means is axially yieldingly connected with an adjacent portion of said turbo-assembly by way of a plug-type connecting means.
Claim 12
Dependent Claim
32 words
An arrangement according to claim 10, wherein said plug-type connecting means includes an extension on said piston means which axially and yieldingly engages in a corresponding opening of said next adjacent portion.
Claim 13
Dependent Claim
19 words
An arrangement according to claim 11, wherein said collar means and said next adjacent portion axially abut one another.
Claim 14
Dependent Claim
37 words
An arrangement according to claim 9, further comprising seal means interposed between said extension and said next adjacent portion for sealing said high gas pressure with respect to the gas pressure immediately downstream of said turbine unit.
Claim 15
Dependent Claim
37 words
An arrangement according to claim 12, further comprising seal means interposed between said extension and said next adjacent portion for sealing said high gas pressure with respect to the gas pressure immediately downstream of said turbine unit.
Claim 16
Dependent Claim
84 words
An arrangement according to claim 1, wherein said facing end surfaces and said high pressure communicating means are so configured that during normal operation of said turbo assembly, the axial pressure forces on said upstream facing end surface approximately equal the axial pressure forces on said downstream facing end surface such that said guide vane means is axially supported at both said inner and outer guide vane rings without bending forces on said guide vane means due to gas flow during said normal operation.
Claim 17
Dependent Claim
83 words
An arrangement according to claim 2, wherein said facing end surfaces and said pressure communicating means are so configured that during normal operatioon of said turbo assembly, the axial pressure forces on said upstream facing end surface approximately equal the axial pressure forces on said downstream facing end surface such that said guide vane means is axially supported at both said inner and outer guide vane rings without bending forces on said guide vane means due to gas flow during said normal operation.
Claim 18
Dependent Claim
36 words
An arrangement according to claim 16, wherein said high pressure communicating means includes means for conducting said high pressure gas from a high pressure compressor of said turbo-assembly which is arranged downstream of said turbine unit.
Claim 19
Dependent Claim
29 words
An arrangement according to claim 15, further comprising seal means for sealing the high gas pressure with respect to the gas pressure prevailing immediately downstream of said turbine unit.
Claim 20
Dependent Claim
27 words
An arrangement according to claim 16, wherein said outer guide vane ring includes a radially outwardly extending protrusion which engages with radial play in said piston means.
Claim 21
Dependent Claim
38 words
An arrangement according to claim 15, wherein a portion of said turbo-assembly including said gas duct and guide vane means is axially yieldingly connected with an adjacent portion of said turbo-assembly by way of a plug-tYpe connecting means.
Claim 22
Dependent Claim
32 words
An arrangement according to claim 20, wherein said plug-type connecting means includes an extension on said piston means which axially and yieldingly engages in a corresponding opening of said next adjacent portion.
Claim 23
Dependent Claim
37 words
An arrangement according to claim 21, further comprising seal means interposed between said extension and said next adjacent portion for sealing said high gas pressure with respect to the gas pressure immediately downstream of said turbine unit.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1976-10-15 | 1977-04-16 | 1977-10-16 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-10-15 | 1981-04-16 | 1981-10-16 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-10-15 | 1985-04-16 | 1985-10-16 | $7700.00 | Window Closed / Lapsed |