US3652177A - Installation for the support of pivotal guide blades - Google Patents
Installation for the support of pivotal guide blades Download PDFInfo
- Publication number
- US3652177A US3652177A US38679A US3652177DA US3652177A US 3652177 A US3652177 A US 3652177A US 38679 A US38679 A US 38679A US 3652177D A US3652177D A US 3652177DA US 3652177 A US3652177 A US 3652177A
- Authority
- US
- United States
- Prior art keywords
- blade
- installation according
- shaft
- annular groove
- bearing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
Definitions
- the present invention relates to an installation for the support of pivotal guide blades of turbo-machines, especially of gas turbines, whereby chambers or passages are provided in a bearing support, through which flows cooling air.
- Particular difficulties have to be overcome in the support of pivotal guide blades of gas turbines, by reason of the large temperature range in which a satisfactory operation must be assured at all times, which difficulties consist in that the bearing clearance necessary for the pivoting movement has to be maintained notwithstanding the considerable thermal expansions.
- a blade shaft constructed as adjusting or actuating shaft be provided with annular grooves in its central bearing portion and at the blade end, which are connected with each other by a thread with cylindrical external surfaces, whereby the central annular groove is in communication with the chambers or passages conducting the cooling air and the annular groove at the blade side is in communication with the guide blade space of the machine.
- the cooling air which can be derived, for example, from a suitable compressor stage or from a similar air supply, flows through the central bore into the central annular groove of the blade shaft and from there by way of the thread to the blade end of the shaft where it flows off into the guide blade space by way of the second bore.
- the particular advantage of this arrangement resides in that the bearing support is effectively cooled at its hottest place; namely, at the blade shaft itself.
- a further advantage resides in that the blade shaft and bearing bore are kept by the cooling system approximately at the same operating temperature at their contact places whereby the bearing clearance which exists with a cold machine, remains approximately constant over the entire operating range (temperature range) of the machine.
- the blade shaft includes, starting from its central annular groove toward the outside, a labyrinth seal having cylindrical external surfaces and consisting of a large number of annular grooves.
- the labyrinth is advantageously formed by a number of annular grooves of rectangular cross-section.
- the blade shaft is constructed as hollow shaft which results in a relatively slight heat flow from the blade through the shaft so that the ratio of heat transferred to the bearing place to the heat removed by cooling can be kept small.
- a bearing bush with good anti-friction properties is inserted between the bearing support and the blade shaft, which bush is provided with inlet and outlet bores or ports for the cooling air corresponding to the bores in the bearing support.
- a bearing bush between housing and adjusting shaft offers the advantage that a material can be selected for the bearing bush which, first of all, has good anti-friction properties that do not change or change only slightly over a certain temperature range, without requiring at the same time high strength properties as are required, for example, in connection with the housing material.
- the good anti-friction properties must be ensured by a suitable material combination since a reduction of the friction by, a lubricant must be considered impractical,
- a favorable low friction clearance conditioned on the material can be attained at the blade adjusting shaft which results correspondingly in slight adjusting forces (moments).
- the bearing bush is provided at its blade end with an offset of reduced diametric dimension so that an inwardly open annular space results between the housing bore and bearing bush, through which the cooling air leaving the bearing bush is conducted into the main gas stream of the turbo-machine. Retuming the cooling air into the guide blade space through such an annular space offers the advantage that any combustion residues which are deposited in the annular gap between the upper guide blade end and the housing bore, are constantly blown off by the inwardly directed air stream and are returned to the main gas stream.
- the blade shaft is provided at its blade end with an annular collar that abuts at the inner end face of the housing or of the bearing bush.
- An outwardly directed pressure force results at the annular collar from the gas pressure in the guide blade space which presses the annular collar against the end surface of the housing or bearing bush so that a good seal of the guide blade space with respect to the bearing place is realized.
- a spring prestressed in the axial direction is provided which is supported on the outer side of the bearing support, on the one hand, and on the blade shaft, on the other.
- This spring pulls the blade shaft outwardly with its prestress so that it causes an abutment of the annular collar of the blade shaft at the inner end face of the bearing bush or housing also with a slight excess pressure in the guide blade space and thus assures a good sealing effect.
- the single FIGURE is a partial cross-sectional view through a guide blade adjusting mechanism of a gas turbine with a bearing bush in accordance with the present invention.
- a bearing bush 3 is securely fitted into a bore 21 provided in a housing 2 forming a bearing support.
- a bore or port 5 is disposed approximately in the center of the bush 3 which is in communication by way of a further bore or port 25 in the housing 2 with a cooling air passage 4 of the housing.
- the bush 3 is provided with a reduced diametric portion forming an offset 23 so that an annular space 22 remains between the bore 21 and the bush 3 at this place.
- One or several radial bores 6 of the bush 3 terminate in this annular space 22.
- the shaft of the guide blade 9 constructed as actuating or adjusting shaft 7 is supported in the bush 3.
- the guide blade shaft 7 is provided at its blade end with an annular collar 8 and adjoining the same with an annular groove 18.
- the shaft 7 is provided in the central area thereof, at the place of the bore 5 of the bush 3, with an annular groove 16.
- This annular groove 16 is in communication with the annular groove 18 by way of several threads of trapezoidal cross-section such as ACME thread form.
- the support of the shaft 7 takes place at the cylindrical outer surfaces of the thread 17 within the bearing bush 3.
- the shaft surface Extending outwardly from the annular groove 16, the shaft surface is provided with a number of annular grooves 20 constructed as labyrinth seal.
- a pivot or actuating lever 13 is clampingly secured to the outer end 12 of the blade shaft 7.
- this adjusting lever 13 takes place by an adjusting or actuating ring 14 arranged at the housing 2.
- An axially prestressed disk or cup spring is provided between the lever 13 and the outer end face of the bush 3, on which rests a closure disk or carrying washer 10a; the prestress force of the spring 10 is transmitted by way of the lever 13 to the blade shaft 7 so that the annular collar 8 of the shaft 7 is pressed against the end surface 30 of the bush 3, located at the inner side of the housing.
- the cooling air flows inwardly and outwardly, following the pressure drop, and more particularly inwardly by way of the thread 17 whereby it cools in an effective manner the blade shaft 7 and the bush 3.
- the cooling air reaches the annular groove 18 from where'it flows off by way of the bore 6 into the annular space 22 and from there into the main stream duct 1.
- a very small amount of compressed air flows from the annular groove 16 in the outward direction by way of the labyrinth seal 20 and exits into the atmosphere at the spring 10 by way of gaps.
- An installation for supporting pivotal guide blades of turbo-machines in which at least one passage is provided in a bearing support through which flows cooling air, characterized in that a blade shaft constructed as an adjusting shaft is provided with annular grooves in its central bearing area and near the blade end thereof, which are in communication with each other by way of a thread, the central annular groove being in communication with the passage conducting the cooling air while the annular groove near the blade end is in communication with the guide blade space of the machine.
- blade shaft is provided near the blade end thereofwith.
- An installation according to claim 12 characterized in that an axially prestressed spring means is provided which is supported, on the one hand, on the outer side of'the bearing support and, on the other, at the blade shaft.
- An installation for supporting pivotal guide blades of turbo-machines comprising a blade shaft formed as an adjusting shaft carrying a blade at one end thereof, a bearing support surrounding said shaft and having at least one passage for conducting cooling air, said shaft being provided with an annular groove in its central bearing area and an annular groove near the bladeend thereof, the central annular groove being in communication with the passage conducting the cooling air while the annular groove near the blade end is in communication with the guide blade space of the machine, the portion-of said blade shaft between the central and blade end grooves being provided with a helical thread for communication therebetween.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Turbines (AREA)
Abstract
An installation for the pivotal support of guide blades of turbo machines particularly gas turbines in which chambers or passages are provided in the bearing support through which flows the cooling air; the blade shaft constructed as adjusting shaft is provided with an annular groove in its center bearing area and with another annular groove at the blade end whereby the two annular grooves are connected with each other by a thread; the central annular groove is in communication with the chambers or passages while the other annular groove is in communication with the guide blade space of the machine.
Description
United States Patent Loebel 1 Mar. 28, 1972 [54] INSTALLATION FOR THE SUPPORT OF PIVOTAL GUIDE BLADES [72] Inventor: Woli Loebel, Munich, Germany AssigneeI Mqtorsmu urhinenrllnion Mun h GmbH, Germany [22] Filed: May 19,1970
[52] U.S.Cl ..415/110,415/116,415/147,
[51] Int. Cl ..F01d 1l/00, F04d 27/00 [58] Field ofSearch ..415/109,110,111, 112,116, 415/115, 149, 150, 156; 416/95, 96, 97,156
[56] References Cited UNITED STATES PATENTS 3,525,574 8/1970 Zerlauth...
1,770,496 7/1930 Lawaczeck ..415/ 169 3,367,628 2/1968 Fitton ..415/110 FOREIGN PATENTS OR APPLICATIONS 755,527 8/1956 Great Britain ..415/156 Primary Examiner-l-lenry F. Raduazo Attorney-Craig, Antonelli and Hill 1 ABSTRACT An installation for the pivotal support of guide blades of turbo machines particularly gas turbines in which chambers or passages are provided in the bearing support through which flows the cooling air; the blade shaft constructed as adjusting shaft is provided with an annular groove in its center bearing area and with another annular groove at the blade end whereby the two annular grooves are connected with each .other by a thread; the central annular groove is in communication with the chambers or passages while the other annular groove'is in communication with the guide blade space of the machine.
18 Claims, 1 Drawing Figure INSTALLATION FOR THE SUPPORT OF PIVOTAL GUIDE BLADES The present invention relates to an installation for the support of pivotal guide blades of turbo-machines, especially of gas turbines, whereby chambers or passages are provided in a bearing support, through which flows cooling air. Particular difficulties have to be overcome in the support of pivotal guide blades of gas turbines, by reason of the large temperature range in which a satisfactory operation must be assured at all times, which difficulties consist in that the bearing clearance necessary for the pivoting movement has to be maintained notwithstanding the considerable thermal expansions.
It is known to cool the bearing places with compressed air in order to avoid large thermal expansions and the danger connected therewith of a binding of the guide blades. The heretofore known arrangements, however, provide only cooling passages or chambers in the bearing housing whereby the cooling flow frequently cannot be conducted sufficiently close to the hottest and therewith the most endangered places of the bearing so that the desired cooling effect is completely absent or is attained only unsatisfactorily.
It is therefore the object of the present invention to provide a bearing support installation for guide blades, in which a cooling medium is conducted directly to the hottest places of the bearing and thus an effective cooling of the bearing is achieved.
As solution to the underlying problems, it is proposed in accordance with the present invention that a blade shaft constructed as adjusting or actuating shaft be provided with annular grooves in its central bearing portion and at the blade end, which are connected with each other by a thread with cylindrical external surfaces, whereby the central annular groove is in communication with the chambers or passages conducting the cooling air and the annular groove at the blade side is in communication with the guide blade space of the machine.
The cooling air, which can be derived, for example, from a suitable compressor stage or from a similar air supply, flows through the central bore into the central annular groove of the blade shaft and from there by way of the thread to the blade end of the shaft where it flows off into the guide blade space by way of the second bore. The particular advantage of this arrangement resides in that the bearing support is effectively cooled at its hottest place; namely, at the blade shaft itself.
A further advantage resides in that the blade shaft and bearing bore are kept by the cooling system approximately at the same operating temperature at their contact places whereby the bearing clearance which exists with a cold machine, remains approximately constant over the entire operating range (temperature range) of the machine.
Finally, an extradordinarily favorable sealing of the guide blade space with respect to the surrounding area is achieved simultaneously by the cooling air guide system of the present invention since the cooling air has simultaneously the effect of a sealing medium.
In an appropriate construction of the present invention, the blade shaft includes, starting from its central annular groove toward the outside, a labyrinth seal having cylindrical external surfaces and consisting of a large number of annular grooves. The labyrinth is advantageously formed by a number of annular grooves of rectangular cross-section. With this type of labyrinth, the cooling air flow from the shaft center in the outward direction is kept as small as possible since it is only of subordinate significance for a cooling effect within this area and the cooling medium mass flow, which represents a loss, should be kept as small as possible.
According to a further feature of the present invention, the blade shaft is constructed as hollow shaft which results in a relatively slight heat flow from the blade through the shaft so that the ratio of heat transferred to the bearing place to the heat removed by cooling can be kept small.
According to a further favorable construction of the bearing support installation according to the present invention, a bearing bush with good anti-friction properties is inserted between the bearing support and the blade shaft, which bush is provided with inlet and outlet bores or ports for the cooling air corresponding to the bores in the bearing support.
The use of a bearing bush between housing and adjusting shaft offers the advantage that a material can be selected for the bearing bush which, first of all, has good anti-friction properties that do not change or change only slightly over a certain temperature range, without requiring at the same time high strength properties as are required, for example, in connection with the housing material. The good anti-friction properties must be ensured by a suitable material combination since a reduction of the friction by, a lubricant must be considered impractical, Thus, by the use of anti-friction bushes, a favorable low friction clearance conditioned on the material can be attained at the blade adjusting shaft which results correspondingly in slight adjusting forces (moments).
According to a further feature of the present invention, the bearing bush is provided at its blade end with an offset of reduced diametric dimension so that an inwardly open annular space results between the housing bore and bearing bush, through which the cooling air leaving the bearing bush is conducted into the main gas stream of the turbo-machine. Retuming the cooling air into the guide blade space through such an annular space offers the advantage that any combustion residues which are deposited in the annular gap between the upper guide blade end and the housing bore, are constantly blown off by the inwardly directed air stream and are returned to the main gas stream.
According to a further development of the present invention, the blade shaft is provided at its blade end with an annular collar that abuts at the inner end face of the housing or of the bearing bush. An outwardly directed pressure force results at the annular collar from the gas pressure in the guide blade space which presses the annular collar against the end surface of the housing or bearing bush so that a good seal of the guide blade space with respect to the bearing place is realized.
In an advantageous manner according to a further feature of the present invention, a spring prestressed in the axial direction is provided which is supported on the outer side of the bearing support, on the one hand, and on the blade shaft, on the other. This spring pulls the blade shaft outwardly with its prestress so that it causes an abutment of the annular collar of the blade shaft at the inner end face of the bearing bush or housing also with a slight excess pressure in the guide blade space and thus assures a good sealing effect.
These and further objects, features and advantages of the present invention will become more obvious from the following description when taken in connection with the accompanying drawing which shows, for purposes of illustration only, one embodiment in accordance with the present invention, and wherein;
The single FIGURE is a partial cross-sectional view through a guide blade adjusting mechanism of a gas turbine with a bearing bush in accordance with the present invention.
Referring now to the single FIGURE of the drawing, a bearing bush 3 is securely fitted into a bore 21 provided in a housing 2 forming a bearing support. A bore or port 5 is disposed approximately in the center of the bush 3 which is in communication by way of a further bore or port 25 in the housing 2 with a cooling air passage 4 of the housing. At the inner end of the housing, the bush 3 is provided with a reduced diametric portion forming an offset 23 so that an annular space 22 remains between the bore 21 and the bush 3 at this place. One or several radial bores 6 of the bush 3 terminate in this annular space 22. The shaft of the guide blade 9 constructed as actuating or adjusting shaft 7 is supported in the bush 3. The guide blade shaft 7 is provided at its blade end with an annular collar 8 and adjoining the same with an annular groove 18. The shaft 7 is provided in the central area thereof, at the place of the bore 5 of the bush 3, with an annular groove 16. This annular groove 16 is in communication with the annular groove 18 by way of several threads of trapezoidal cross-section such as ACME thread form. The support of the shaft 7 takes place at the cylindrical outer surfaces of the thread 17 within the bearing bush 3. Extending outwardly from the annular groove 16, the shaft surface is provided with a number of annular grooves 20 constructed as labyrinth seal. A pivot or actuating lever 13 is clampingly secured to the outer end 12 of the blade shaft 7. The pivoting of this adjusting lever 13 takes place by an adjusting or actuating ring 14 arranged at the housing 2. An axially prestressed disk or cup spring is provided between the lever 13 and the outer end face of the bush 3, on which rests a closure disk or carrying washer 10a; the prestress force of the spring 10 is transmitted by way of the lever 13 to the blade shaft 7 so that the annular collar 8 of the shaft 7 is pressed against the end surface 30 of the bush 3, located at the inner side of the housing.
The compressed air supplied by an air source and flowing through one or several passages 15 into the space 4, flows through the bores and 5 into the annular groove 16 between the bush 3 and the blade shaft 7.
From there, the cooling air flows inwardly and outwardly, following the pressure drop, and more particularly inwardly by way of the thread 17 whereby it cools in an effective manner the blade shaft 7 and the bush 3. After leaving the thread 17, the cooling air reaches the annular groove 18 from where'it flows off by way of the bore 6 into the annular space 22 and from there into the main stream duct 1. A very small amount of compressed air flows from the annular groove 16 in the outward direction by way of the labyrinth seal 20 and exits into the atmosphere at the spring 10 by way of gaps.
While I have shown and described only one embodiment in accordance with the present invention, it is understood that the same is not limited thereto but is susceptible of numerous changes and modifications as known to those skilled in the art, and I therefore do not wish to be limited to the details shown and described herein but intend to cover all such changes and modifications as are encompassed by the scope of the ap pended claims.
I claim:
1. An installation for supporting pivotal guide blades of turbo-machines in which at least one passage is provided in a bearing support through which flows cooling air, characterized in that a blade shaft constructed as an adjusting shaft is provided with annular grooves in its central bearing area and near the blade end thereof, which are in communication with each other by way of a thread, the central annular groove being in communication with the passage conducting the cooling air while the annular groove near the blade end is in communication with the guide blade space of the machine.
2. An installation according to claim 1, characterized in that said thread has substantially cylindrical external surfaces.
3. An installation according to claim 2, characterized in that the blade shaft, starting from the central annular groove in the outward direction, is provided with a labyrinth seal means consisting of a number of annular grooves.
4. An installation according to claim 3, characterized in that the labyrinth seal means has cylindrical outer surfaces.
5. An installation according to claim 4, characterized in that the blade shaft is constructed as a hollow shaft.
6. An installation according to claim 5, characterized in that a bearing bush means with good anti-friction properties is inserted between the bearing support and the blade shaft, said bush means being provided with inlet and discharge bores for the cooling air corresponding to the support means.
7. An installation according to claim 6, characterized in that the bearing bush means is provided near the blade end with a portion of reduced diametric dimension so that an inwardly the blade shaft is provided near the blade end thereof with an annular. collar that abuts at the inner end face of one of the two parts consisting of housing and bearing bush means.
9. An installation according to claim 8, characterized in that an axially prestressed spring means is provided which is supported, on the one hand, on the'outer side of the bearing supportand, on the other, at the blade shalt.
10. An installation according to claim 1, characterized in that a bearing bush means with good anti-friction properties is inserted between the bearing support and the blade shah, said bush means being provided with inlet and discharge bores for the cooling air corresponding to the support means.
11. An installation according to claim 10, characterized in that the bearing bush means is provided near the blade end with a portion of reduced diametric dimension so that an inwardly open annular space results between the housing bore and the bearing bush means, and in that the cooling air leaving the bearing bushmeans is conducted through the inwardly open annular space into the main flowchannel of the turbo machine.
12 An installation according to claim 1, characterized, in
that the blade shaft is provided near the blade end thereofwith.
an annular collar that abuts at the inner end face of one of the two parts consisting of housing and bearing bush means. 1
, '13. An installation according to claim 12, characterized in that an axially prestressed spring means is provided which is supported, on the one hand, on the outer side of'the bearing support and, on the other, at the blade shaft.
14. An installation according to claim 12, characterized in that the blade shaft, starting from the central annular groove in the outward direction, is provided with a labyrinth seal means consisting of a number of annular grooves.
15. An installation according to claim 1, characterized in that an axially prestressed spring means is provided which is supported, on the one hand, on the outer side of the bearing support and, on the other, at the blade shaft.
16. An installation according to claim 1, characterized in that the blade shaft, starting from the central annular groove in the outward direction, is provided with a labyrinth seal means consisting of a number of annular grooves.
17. An installation for supporting pivotal guide blades of turbo-machines, comprising a blade shaft formed as an adjusting shaft carrying a blade at one end thereof, a bearing support surrounding said shaft and having at least one passage for conducting cooling air, said shaft being provided with an annular groove in its central bearing area and an annular groove near the bladeend thereof, the central annular groove being in communication with the passage conducting the cooling air while the annular groove near the blade end is in communication with the guide blade space of the machine, the portion-of said blade shaft between the central and blade end grooves being provided with a helical thread for communication therebetween.
18. An installation according to claim 17, wherein the portion of said shaft extending from the central annular groove in the outward direction is provided with a labyrinth seal means in the form of a plurality of annular grooves for preventing the flow of cooling air.
* i it
Claims (18)
1. An installation for supporting pivotal guide blades of turbomachines in which at least one passage is provided in a bearing support through which Flows cooling air, characterized in that a blade shaft constructed as an adjusting shaft is provided with annular grooves in its central bearing area and near the blade end thereof, which are in communication with each other by way of a thread, the central annular groove being in communication with the passage conducting the cooling air while the annular groove near the blade end is in communication with the guide blade space of the machine.
2. An installation according to claim 1, characterized in that said thread has substantially cylindrical external surfaces.
3. An installation according to claim 2, characterized in that the blade shaft, starting from the central annular groove in the outward direction, is provided with a labyrinth seal means consisting of a number of annular grooves.
4. An installation according to claim 3, characterized in that the labyrinth seal means has cylindrical outer surfaces.
5. An installation according to claim 4, characterized in that the blade shaft is constructed as a hollow shaft.
6. An installation according to claim 5, characterized in that a bearing bush means with good anti-friction properties is inserted between the bearing support and the blade shaft, said bush means being provided with inlet and discharge bores for the cooling air corresponding to the support means.
7. An installation according to claim 6, characterized in that the bearing bush means is provided near the blade end with a portion of reduced diametric dimension so that an inwardly open annular space results between the housing bore and the bearing bush means, and in that the cooling air leaving the bearing bush means is conducted through the inwardly open annular space into the main flow channel of the turbo-machine.
8. An installation according to claim 7, characterized in that the blade shaft is provided near the blade end thereof with an annular collar that abuts at the inner end face of one of the two parts consisting of housing and bearing bush means.
9. An installation according to claim 8, characterized in that an axially prestressed spring means is provided which is supported, on the one hand, on the outer side of the bearing support and, on the other, at the blade shaft.
10. An installation according to claim 1, characterized in that a bearing bush means with good anti-friction properties is inserted between the bearing support and the blade shaft, said bush means being provided with inlet and discharge bores for the cooling air corresponding to the support means.
11. An installation according to claim 10, characterized in that the bearing bush means is provided near the blade end with a portion of reduced diametric dimension so that an inwardly open annular space results between the housing bore and the bearing bush means, and in that the cooling air leaving the bearing bush means is conducted through the inwardly open annular space into the main flow channel of the turbo-machine.
12. An installation according to claim 1, characterized in that the blade shaft is provided near the blade end thereof with an annular collar that abuts at the inner end face of one of the two parts consisting of housing and bearing bush means.
13. An installation according to claim 12, characterized in that an axially prestressed spring means is provided which is supported, on the one hand, on the outer side of the bearing support and, on the other, at the blade shaft.
14. An installation according to claim 12, characterized in that the blade shaft, starting from the central annular groove in the outward direction, is provided with a labyrinth seal means consisting of a number of annular grooves.
15. An installation according to claim 1, characterized in that an axially prestressed spring means is provided which is supported, on the one hand, on the outer side of the bearing support and, on the other, at the blade shaft.
16. An installation according to claim 1, characterized in that the blade shaft, starting from the central annular gRoove in the outward direction, is provided with a labyrinth seal means consisting of a number of annular grooves.
17. An installation for supporting pivotal guide blades of turbo-machines, comprising a blade shaft formed as an adjusting shaft carrying a blade at one end thereof, a bearing support surrounding said shaft and having at least one passage for conducting cooling air, said shaft being provided with an annular groove in its central bearing area and an annular groove near the blade end thereof, the central annular groove being in communication with the passage conducting the cooling air while the annular groove near the blade end is in communication with the guide blade space of the machine, the portion of said blade shaft between the central and blade end grooves being provided with a helical thread for communication therebetween.
18. An installation according to claim 17, wherein the portion of said shaft extending from the central annular groove in the outward direction is provided with a labyrinth seal means in the form of a plurality of annular grooves for preventing the flow of cooling air.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19691926327 DE1926327C (en) | 1969-05-23 | Bearing of pivotable guide vanes |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US3652177A true US3652177A (en) | 1972-03-28 |
Family
ID=5734972
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US38679A Expired - Lifetime US3652177A (en) | 1969-05-23 | 1970-05-19 | Installation for the support of pivotal guide blades |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US3652177A (en) |
| FR (1) | FR2030895A5 (en) |
| GB (1) | GB1249279A (en) |
| SE (1) | SE358441B (en) |
Cited By (25)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3788763A (en) * | 1972-11-01 | 1974-01-29 | Gen Motors Corp | Variable vanes |
| US3966352A (en) * | 1975-06-30 | 1976-06-29 | United Technologies Corporation | Variable area turbine |
| US4007998A (en) * | 1975-08-22 | 1977-02-15 | Carrier Corporation | Blade assembly |
| US4025227A (en) * | 1975-06-30 | 1977-05-24 | United Technologies Corporation | Variable area turbine |
| US4522557A (en) * | 1982-01-07 | 1985-06-11 | S.N.E.C.M.A. | Cooling device for movable turbine blade collars |
| US4767264A (en) * | 1986-10-31 | 1988-08-30 | United Technologies Corporation | Vane lever arm construction |
| US4810165A (en) * | 1986-07-09 | 1989-03-07 | Mtu Motoren- Und Turbinen-Union Munchen Gmbh | Adjusting mechanism for guide blades of turbo-propulsion units |
| US4861228A (en) * | 1987-10-10 | 1989-08-29 | Rolls-Royce Plc | Variable stator vane assembly |
| US5498128A (en) * | 1993-03-25 | 1996-03-12 | Abb Management Ag | Radial-flow exhaust gas turbocharger turbine with adjustable guide vanes |
| US5518365A (en) * | 1993-03-25 | 1996-05-21 | Abb Management Ag | Radial-flow exhaust gas turbocharger turbine with adjustable guide vanes |
| US5622473A (en) * | 1995-11-17 | 1997-04-22 | General Electric Company | Variable stator vane assembly |
| US20010026758A1 (en) * | 2000-04-04 | 2001-10-04 | Man B&W Diesel Aktiengesellschaft | Flow duct guide apparatus for an axial flow trubine |
| EP1217173A2 (en) * | 2000-12-20 | 2002-06-26 | United Technologies Corporation | Vane for use in turbo machines |
| US6443694B1 (en) * | 1998-05-28 | 2002-09-03 | Abb | Rotor machine device |
| EP1256697A2 (en) * | 2001-05-11 | 2002-11-13 | FIATAVIO S.p.A. | Stator vane of a variable-geometry turbine |
| EP1382804A2 (en) * | 2002-07-16 | 2004-01-21 | AVIO S.p.A. | Hinge device for a rotary member of an aircraft engine |
| US20070160463A1 (en) * | 2005-08-26 | 2007-07-12 | Ingo Jahns | Gap control arrangement for a gas turbine |
| US20100018219A1 (en) * | 2006-06-01 | 2010-01-28 | Moreno Baldaccini | Device for optimizing cooling in gas turbines |
| US20120093632A1 (en) * | 2010-10-15 | 2012-04-19 | General Electric Company | Variable turbine nozzle system |
| US20120121403A1 (en) * | 2009-07-20 | 2012-05-17 | Cameron International Corporation | Removable throat mounted inlet guide vane |
| US9200640B2 (en) | 2009-11-03 | 2015-12-01 | Ingersoll-Rand Company | Inlet guide vane for a compressor |
| US20160222825A1 (en) * | 2013-10-03 | 2016-08-04 | United Technologies Corporation | Rotating turbine vane bearing cooling |
| US20160376915A1 (en) * | 2015-06-25 | 2016-12-29 | Rolls-Royce Deutschland Ltd & Co Kg | Stator device for a continuous-flow machine with a housing appliance and multiple guide vanes |
| US20160376916A1 (en) * | 2015-06-25 | 2016-12-29 | Rolls-Royce Deutschland Ltd & Co Kg | Stator device for a continuous-flow machine with a housing appliance and multiple guide vanes |
| US10711817B2 (en) * | 2016-06-14 | 2020-07-14 | EMC IP Holding Company LLC | Rod for use in rack and holding device for use in cooperation with rack |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4214852A (en) * | 1978-04-20 | 1980-07-29 | General Electric Company | Variable turbine vane assembly |
| DE2931766C2 (en) * | 1979-08-04 | 1982-08-05 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Sealing device for the free blade ends of an adjustable diffuser of a gas turbine |
| FR2570133A1 (en) * | 1984-09-12 | 1986-03-14 | Szydlowski Joseph | Device for directing a flow of air at any point over an entire blade height at the inlet of a wheel of an axial compressor |
| GB2339244B (en) * | 1998-06-19 | 2002-12-18 | Rolls Royce Plc | A variable camber vane |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1770496A (en) * | 1916-08-25 | 1930-07-15 | Worthington Pump & Mach Corp | Shaft packing |
| GB755527A (en) * | 1953-10-15 | 1956-08-22 | Power Jets Res & Dev Ltd | Mounting of swivelling guide vane elements in axial flow elastic fluid turbines |
| US3367628A (en) * | 1966-10-31 | 1968-02-06 | United Aircraft Corp | Movable vane unit |
| US3525574A (en) * | 1968-07-26 | 1970-08-25 | Sulzer Ag | Vane ring for turbo-engines |
-
1969
- 1969-12-18 FR FR6943948A patent/FR2030895A5/fr not_active Expired
-
1970
- 1970-05-19 US US38679A patent/US3652177A/en not_active Expired - Lifetime
- 1970-05-22 GB GB25024/70A patent/GB1249279A/en not_active Expired
- 1970-05-25 SE SE07161/70A patent/SE358441B/xx unknown
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1770496A (en) * | 1916-08-25 | 1930-07-15 | Worthington Pump & Mach Corp | Shaft packing |
| GB755527A (en) * | 1953-10-15 | 1956-08-22 | Power Jets Res & Dev Ltd | Mounting of swivelling guide vane elements in axial flow elastic fluid turbines |
| US3367628A (en) * | 1966-10-31 | 1968-02-06 | United Aircraft Corp | Movable vane unit |
| US3525574A (en) * | 1968-07-26 | 1970-08-25 | Sulzer Ag | Vane ring for turbo-engines |
Cited By (37)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3788763A (en) * | 1972-11-01 | 1974-01-29 | Gen Motors Corp | Variable vanes |
| US3966352A (en) * | 1975-06-30 | 1976-06-29 | United Technologies Corporation | Variable area turbine |
| US4025227A (en) * | 1975-06-30 | 1977-05-24 | United Technologies Corporation | Variable area turbine |
| US4007998A (en) * | 1975-08-22 | 1977-02-15 | Carrier Corporation | Blade assembly |
| US4522557A (en) * | 1982-01-07 | 1985-06-11 | S.N.E.C.M.A. | Cooling device for movable turbine blade collars |
| US4810165A (en) * | 1986-07-09 | 1989-03-07 | Mtu Motoren- Und Turbinen-Union Munchen Gmbh | Adjusting mechanism for guide blades of turbo-propulsion units |
| US4767264A (en) * | 1986-10-31 | 1988-08-30 | United Technologies Corporation | Vane lever arm construction |
| US4861228A (en) * | 1987-10-10 | 1989-08-29 | Rolls-Royce Plc | Variable stator vane assembly |
| US5498128A (en) * | 1993-03-25 | 1996-03-12 | Abb Management Ag | Radial-flow exhaust gas turbocharger turbine with adjustable guide vanes |
| US5518365A (en) * | 1993-03-25 | 1996-05-21 | Abb Management Ag | Radial-flow exhaust gas turbocharger turbine with adjustable guide vanes |
| US5622473A (en) * | 1995-11-17 | 1997-04-22 | General Electric Company | Variable stator vane assembly |
| US6443694B1 (en) * | 1998-05-28 | 2002-09-03 | Abb | Rotor machine device |
| US20010026758A1 (en) * | 2000-04-04 | 2001-10-04 | Man B&W Diesel Aktiengesellschaft | Flow duct guide apparatus for an axial flow trubine |
| US6547521B2 (en) * | 2000-04-04 | 2003-04-15 | Man B&W Diesel Aktiengesellschaft | Flow duct guide apparatus for an axial flow turbine |
| EP1217173A2 (en) * | 2000-12-20 | 2002-06-26 | United Technologies Corporation | Vane for use in turbo machines |
| EP1217173A3 (en) * | 2000-12-20 | 2003-10-29 | United Technologies Corporation | Vane for use in turbo machines |
| EP1256697A3 (en) * | 2001-05-11 | 2004-03-10 | AVIO S.p.A. | Stator vane of a variable-geometry turbine |
| EP1256697A2 (en) * | 2001-05-11 | 2002-11-13 | FIATAVIO S.p.A. | Stator vane of a variable-geometry turbine |
| US20040107538A1 (en) * | 2002-07-16 | 2004-06-10 | Avio S.P.A. | Hinge device for a rotary member of an aircraft engine |
| EP1382804A3 (en) * | 2002-07-16 | 2004-09-15 | AVIO S.p.A. | Hinge device for a rotary member of an aircraft engine |
| EP1382804A2 (en) * | 2002-07-16 | 2004-01-21 | AVIO S.p.A. | Hinge device for a rotary member of an aircraft engine |
| US20070160463A1 (en) * | 2005-08-26 | 2007-07-12 | Ingo Jahns | Gap control arrangement for a gas turbine |
| US20100018219A1 (en) * | 2006-06-01 | 2010-01-28 | Moreno Baldaccini | Device for optimizing cooling in gas turbines |
| US8453465B2 (en) * | 2006-06-01 | 2013-06-04 | Nuovo Pignone, S.P.A. | Device for optimizing cooling in gas turbines |
| US9243648B2 (en) * | 2009-07-20 | 2016-01-26 | Ingersoll-Rand Company | Removable throat mounted inlet guide vane |
| US20120121403A1 (en) * | 2009-07-20 | 2012-05-17 | Cameron International Corporation | Removable throat mounted inlet guide vane |
| CN102575684A (en) * | 2009-07-20 | 2012-07-11 | 卡梅伦国际公司 | Removable throat mounted inlet guide vane |
| US9200640B2 (en) | 2009-11-03 | 2015-12-01 | Ingersoll-Rand Company | Inlet guide vane for a compressor |
| US8668445B2 (en) * | 2010-10-15 | 2014-03-11 | General Electric Company | Variable turbine nozzle system |
| US20120093632A1 (en) * | 2010-10-15 | 2012-04-19 | General Electric Company | Variable turbine nozzle system |
| DE102011054468B4 (en) * | 2010-10-15 | 2021-05-20 | General Electric Company | Variable turbine nozzle system |
| US20160222825A1 (en) * | 2013-10-03 | 2016-08-04 | United Technologies Corporation | Rotating turbine vane bearing cooling |
| US10830096B2 (en) * | 2013-10-03 | 2020-11-10 | Raytheon Technologies Corporation | Rotating turbine vane bearing cooling |
| US20160376915A1 (en) * | 2015-06-25 | 2016-12-29 | Rolls-Royce Deutschland Ltd & Co Kg | Stator device for a continuous-flow machine with a housing appliance and multiple guide vanes |
| US20160376916A1 (en) * | 2015-06-25 | 2016-12-29 | Rolls-Royce Deutschland Ltd & Co Kg | Stator device for a continuous-flow machine with a housing appliance and multiple guide vanes |
| US10344616B2 (en) * | 2015-06-25 | 2019-07-09 | Rolls-Royce Deutschland Ltd & Co Kg | Stator device for a continuous-flow machine with a housing appliance and multiple guide vanes |
| US10711817B2 (en) * | 2016-06-14 | 2020-07-14 | EMC IP Holding Company LLC | Rod for use in rack and holding device for use in cooperation with rack |
Also Published As
| Publication number | Publication date |
|---|---|
| SE358441B (en) | 1973-07-30 |
| GB1249279A (en) | 1971-10-13 |
| FR2030895A5 (en) | 1970-11-13 |
| DE1926327A1 (en) | 1970-12-03 |
| DE1926327B2 (en) | 1972-09-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US3652177A (en) | Installation for the support of pivotal guide blades | |
| US3825364A (en) | Porous abradable turbine shroud | |
| US3674377A (en) | Guide blading for turbo machines with adjustable guide vanes | |
| US2630673A (en) | Cooling means for variable area nozzles | |
| US6126390A (en) | Passive clearance control system for a gas turbine | |
| KR100537036B1 (en) | Centrifugal compressor | |
| US4156342A (en) | Cooling apparatus for a bearing in a gas turbine | |
| US3391904A (en) | Optimum response tip seal | |
| US3312448A (en) | Seal arrangement for preventing leakage of lubricant in gas turbine engines | |
| US5564896A (en) | Method and apparatus for shaft sealing and for cooling on the exhaust-gas side of an axial-flow gas turbine | |
| US4930980A (en) | Cooled turbine vane | |
| US5557920A (en) | Combustor bypass system for a gas turbine | |
| US5517817A (en) | Variable area turbine nozzle for turbine engines | |
| US4425079A (en) | Air sealing for turbomachines | |
| US6226975B1 (en) | Turbine power plant having a floating brush seal | |
| US8177475B2 (en) | Contaminant-deflector labyrinth seal and method of operation | |
| US6234746B1 (en) | Apparatus and methods for cooling rotary components in a turbine | |
| US3647311A (en) | Turbine interstage seal assembly | |
| EP2419609B1 (en) | Cooled one piece casing of a turbo machine | |
| US4785624A (en) | Turbine engine blade variable cooling means | |
| US5311734A (en) | System and method for improved engine cooling in conjunction with an improved gas bearing face seal assembly | |
| JP6185781B2 (en) | Axial flow compressor | |
| US20100139288A1 (en) | Heat exchanger to cool turbine air cooling flow | |
| US3966352A (en) | Variable area turbine | |
| US4668163A (en) | Automatic control device of a labyrinth seal clearance in a turbo-jet engine |