CA1187810A - Cooled combustion turbine blade with retrofit blade seal - Google Patents
Cooled combustion turbine blade with retrofit blade sealInfo
- Publication number
- CA1187810A CA1187810A CA000410997A CA410997A CA1187810A CA 1187810 A CA1187810 A CA 1187810A CA 000410997 A CA000410997 A CA 000410997A CA 410997 A CA410997 A CA 410997A CA 1187810 A CA1187810 A CA 1187810A
- Authority
- CA
- Canada
- Prior art keywords
- blade
- disc
- root
- turbine
- plenum chamber
- 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
Links
Abstract
ABSTRACT OF THE DISCLOSURE
The invention comprises a retrofit turbine blade cooling apparatus for replacing non-cooled turbine blades in presently existing combustion turbines. The cooling apparatus comprises a turbine blade structured for fluid cooling and a sealing apparatus structured to cooperate with a root portion of the turbine blade and a subadjacent portion of a turbine disc to force cooling fluid into the turbine blade. Use of the cooling apparatus requires no modification or disassembly of the rotor assembly.
The invention comprises a retrofit turbine blade cooling apparatus for replacing non-cooled turbine blades in presently existing combustion turbines. The cooling apparatus comprises a turbine blade structured for fluid cooling and a sealing apparatus structured to cooperate with a root portion of the turbine blade and a subadjacent portion of a turbine disc to force cooling fluid into the turbine blade. Use of the cooling apparatus requires no modification or disassembly of the rotor assembly.
Description
7~a 1 ~9,5 COOLED CO~BUSTION TUR~INE BLADE
WITH RETROFIT BLADE SEAL
BACKGROUND OF THE INVENTION
The present invention relates generally to com~ustion turbine rotor blades and more particularly to a cooled combustion turbine rotor blade which may be back-fitted into a rotor disc originally structured for anon-cooled turbine rotor blade.
It is well established that greater operating efficiency and power output of a combustion turbine may bs achieved through higher -inlet operating temperatures.
Inlet operating temperatures are limited, however, by the maximum temperature tolerable to the rotating turbine blades. Also, as turbine blade temperature increases with increasing inlet gas temperature, the vulnerability o~ the blades to damage from the tension and stresses which normally accompany blade rotation also increases. Cooling the turbine blades, or forming the blades from a tempera-ture resis~ant material, or both, permits an increase in inlet operating temperatures while keeping the turbine blade temp~rature below the maximum specified operating temperature for the blade material.
There are presently many combustion turbines in the field today which have non-cooled turbine rotor blades. In some models the first stage blades are cooled while blades in subsequent stages are not. ~enerally, those combustion turbines which have non-cooled turbine ~ ` .
WITH RETROFIT BLADE SEAL
BACKGROUND OF THE INVENTION
The present invention relates generally to com~ustion turbine rotor blades and more particularly to a cooled combustion turbine rotor blade which may be back-fitted into a rotor disc originally structured for anon-cooled turbine rotor blade.
It is well established that greater operating efficiency and power output of a combustion turbine may bs achieved through higher -inlet operating temperatures.
Inlet operating temperatures are limited, however, by the maximum temperature tolerable to the rotating turbine blades. Also, as turbine blade temperature increases with increasing inlet gas temperature, the vulnerability o~ the blades to damage from the tension and stresses which normally accompany blade rotation also increases. Cooling the turbine blades, or forming the blades from a tempera-ture resis~ant material, or both, permits an increase in inlet operating temperatures while keeping the turbine blade temp~rature below the maximum specified operating temperature for the blade material.
There are presently many combustion turbines in the field today which have non-cooled turbine rotor blades. In some models the first stage blades are cooled while blades in subsequent stages are not. ~enerally, those combustion turbines which have non-cooled turbine ~ ` .
2 g9,596 roto~ blades provide some means for cooling the root of the blades, such as the means set forth in U.S. Patent
3,501,249 and U.~. Patent 3,572,966~ Cooliny the blade root is a simple method ~or providiny partial cooling of the blade airfoi].. The latter patent describes a struc-ture whereby cooling air drawn from the compressor is forced through individual channels in each disc to a path between the blade root and the disc. After passing be-tween the blade root and the disc, the cooling air exits into the exhaust path of the hot motive gases driving the turbine.
To improve the operating efficiency and power output of the combustion turbine, it is desirable to provide means which enables a flow of cooling air through the turbine blades themselves so that the blade surfaces are positively cooled to keep the blade surface tempera-ture below the turbine inlet temperature. A prior art approach to this problem is shown in U.S. Patent No.
3,853,~25. This patent describes an assembly for sealing the exhaust end of the cooling path between the blade root and the disc, forcing the cooling air up through the blade root into the airfoil portion of the turbine blade. The cooling air thereafter exits from the airfoil portion into the exhaust path of the hot motive gases. The sealing assembly of the latter patent comprises a seal structure mating with grooves within the blade root and the disc to close the exhaust end of the cooling path between the blade root and the disc. Hence, use of the apparatus described in the latter patent requires special machining of the rotor disc as well as a specially structured tur-bine blade.
While the sealing assembly described above provides an efficient and effective method for channeling cooling air to the turbine bLade, it is not readily adapt-able to combustion turbines presently in the field.Application of this structure to field units would re~uire structura' ~odifications to both the turbine blade root 71!~
3 49,59~
and the rotor disc. Modification to the rotor disc T~ould necessitate removal of the rotor spindle from the lower half of the turbine casiny. As explained in U.S. Patent No. 3,493,212, the positioning of the rotor is highly critical, so that once it is properly located it should remain undist-lrbed if at all possible. Removal of the rotor splndle also increases the time and expense required to implement changes to the combustion turbine.
Hence, it would be advantageous to develop a cooled combustion turbine blade with sealing structure such that it may be backfitted into presently existing rotor discs, thereby providing the advantages of cooled turbine blades without the disadvantages of rotor spindle removal.
SUMMARY OF THE INV~NTION
Accordingly, a combustion turbine rotor blade which has a cooling system and sealing apparatus and is adapted for support on a rotor disc is provided for re-placing non-cooled turbine blades in presently existiny combustion turbines. The turbine blade, with cooling system and sealing apparatus, operates in cooperation with the rotor disc to effect a blade cooling structure in presently existing discs having non-cooled blades. The cooling system comprises means within a blade airfoil and a blade root for conducting coolant fluid therethrough.
The sealing apparatus is structured to affix to the blade root and sealingly close an axially extending chamber formed between the radially innermost portion of the blade root and the rotor disc. The sealing apparatus thereby closes a former exhaust path for coolant fluid and forces the coolant fluid into the turbine blade. Use of the cooled turbine blade requires no modification or disassem-bly of the turbine rotor assembly.
BRIEF D~SCRIPTION OF T~E DRAWINGS
Figure 1 shows a section ~iew of a portion of a typical prior art turbine section of a combustion turbine.
~7~
a 4~, 596 ~ igure 2 shows a section view of a portion of a -turbine bla~e wit~. sealing apparatus and cooLiny system structured according to the principles of the invention.
Figure 3 shows a front perspective vie~" of the sealing apparatus of the invention.
Figure 4 shows a side view of the sealing appar-atus of the invention.
Figure 5 shows a cutaway of Figure 2 in section revealing an upstream view of the cooled turbine blade root and sealing apparatus of the invention in position within the turbine disc.
DESCRIPTION ~F THE PREFERRED EMBODIMENT
Increased combustion turbine operating tempera-tures in presently existing combustion turbines has made it necessary to provide cooled turbine blades where before the blades were not cooled. In accordance with the prin-ciples of the invention, a combustion turbine blade with cooling system and sealing apparatus is provided. The blade is adapted ~or support on and operates in coopera-tion with prior art turbine rotor discs, providing a bladecooling structure for presently operating turbines having discs with non-cooled blades. The cooled turbine blade comprises a turbine blade specially constructed for con-duction of cooling fluid and a sealing apparatus for closing a fluid flow path between the blade root and the disc of the prior art structure and thereby forcing cool-ant 1uid to flow within the modified turbine blade struc-ture.
Referring now to the drawings, Eigure l shows a portion of a typical prior art rotor lO for an axial flow turbine in longitudinal section. The rotor lO may com-prise an aggregate of rotor discs only ~wo of which 12, 14 are shown, secured together by circumferentially disposed tie or staybolts 15 e~tending through the discs, only one tie bolt being shown in Figure l.
The discs 12, ].4 support, respectively, rotor bl-~des 16, 18 extending radially outwardly therefrom, the 8~
~9,596 blades bein~ d sposed between axialLy spaced, in~Jardiy extending fixed stator or nozzle blades 20, 21, 22. The rotor blades arG respectively provided with root portions 26, 28 of the side entry type which may be of the serrated or "fur tree" type for disposition in serrated recesses (see Fig. 5) provided in the periphery of the discs.
The rotor discs 12, 14 are further provided respectively with axially extending openings or channels 30, 32. The channels are in fluid communication with a passageway 33 formed by a tubular fairing member 34 dis-posed in encompassing relation with a center torque tube structure 35.
The discs 12, 14 are provided with circumfer-entially spaced, radially extending openings 40 on the upstream side and near the pariphery thereof. The open-ings 40 are formed in the disc to be in fluid communi-cation with the passa~eway 33.
The upstream side of the disc 12, 14 is further provided with an annular, continuous groove or channel 42 facing in a radially outward direction. The groove is formed in fluid communication with the radially extending openings 40. The detail of this typical prior art struc-ture is further described in U.S. ~atent No. 3,572,966.
Figure 2 shows a portion of the prior art disc 12 with a turbine blade and sealing mechanism structured accordin~ to the principles of the invention. For the purposes of the invention, the structure of disc 12 and disc 14 are substantially identical. The turbine blade 16 compri.ses an airfoil portion 46 and a root portion 26.
The root portion of the turbine blade is secured to the disc by the serrated structure of the blade~disc juncture and by conventional sideplates 48, 50, such as those described in U.S. Patent No. 3,572,966. The annularly disposed upstream sideplates 50, when secured within grooves 52, 54 formed respectively in the disc and blade define a continuous circumferential coolant chamber 4 with the adjacent ends of the roots 26 of the turbine ~8~7~
6 49,596 blades. The coolant chamber 44 is structured in ~luid communication with the continuous channel 42 and the radial openings 40.
In operation of the rotor a pressurized coollng fluid such as air from a compressor section of the com-bustion turbine is directed through the passageway 33 to the first disc 12 (see Figure 1). At the disc 12, the flow of air divides, part of the air traveling through the axial opening 30 in the disc 12 to the second disc 14.
The remainder of the air is directed radi~lly outward (upward in Figure 1 as indicated by the appropriats ar-rows) to the openings 40 beneath the annular groove 42.
From the annular groove 42 the air is then directed into the annular chamber 44 formed by the upstream sideplates and the ends of the blade roots. The flow of air is then directed through the clearances between the blade root and disc recesses and particularly into a plenum chamber 56 formed between the base of the blade root and the turbine disc.
In the typical prior art structure of Figure 1 the cooling air would pass from the plenum chamber 56 through an aperture in the exhaust sideplate 48 and into the e~haust path of the hot motive gases driving the turbine. In the cooling mechanism of the invention, a sealing apparatus 58, shown in greater detail in Figures 3, 4, and 5, closes the exhaust end of the plenum chamber 58, forcing the cooling air into radially extending chan-nels 60 within the turbine blade. The precise arrangement for coolant flow within the root and airfoil portions of the turbine blade is not critical to an understanding of the principles of the invention and may be any of several arrangements well known in the prior art.
The sealing apparatus 58 is structured so as to require no structural modification of the rotor disc 12 for its implementation. Figure 3 shows an upstream per-spective view of the sealing apparatus 5t3 Figure 4 shows a side view OI the same sealing apparatus. The upper por 3'7~
7 49,5~6 tion of the sealing apparatus is shaped to fit continu-ously within the radially innermost serration ~4 (Fig. 5) of the root portion of the turbine blade. The upper portion 62 of the sealing apparatus also defines a rectan-gular notch 66 which permits fixed engagement of thesealing apparatus within the root of the turbine blade.
A lower portion 68 of the sealing apparatus 58 is shaped to fit closely the periphery 70 (Fig. 5) of the plenum chamber 56 so as to seal the downstream end of that chamber. The thickness of the lower portion should be sufficient to assure adequate sealing of the plenum cham-ber but should preferably be no greater than the radial dimens.ion of the lower portion. ~ recess 72 of any con-venient configuration is provided in the lower portion o the sealing apparatus in the face which is adjacent the exhaust sideplate 48. The recess 72 simplifies assembly and disassembly of the sealing apparatus within the blade root and plenum chamber.
The exhaust end of the bottom serration of the blade root is notched as shown in Figure 2 at 74 to permit the upper portion 62 of the sealing apparatus to fit closely within the disc serration. A blade tab 76 inte-gral with the blade root mates with the rectangular notch 66 in the upper portion of the sealing apparatus, re-stricting movement of the sealing apparatus in the axialdirection. The close fitting shape of the sealing appara-tus within the disc serration and plenum chamber restricts movement of the sealing apparatus in the radial direction.
Thus, the combination of a cooled turbine blade and a sealing apparatus, cooperating accordin~ to the principles of the invention, provides a simple and yet effective structure which may be backfitted into presently existing co~bustion turbines having non-cooled blades.
The turbine blade a~d its cooling mechanism set forth herein permit replacement of non-cooled turbine blades with cooled turbine blades without s ructural modification or disturbance of the turbine rotor.
To improve the operating efficiency and power output of the combustion turbine, it is desirable to provide means which enables a flow of cooling air through the turbine blades themselves so that the blade surfaces are positively cooled to keep the blade surface tempera-ture below the turbine inlet temperature. A prior art approach to this problem is shown in U.S. Patent No.
3,853,~25. This patent describes an assembly for sealing the exhaust end of the cooling path between the blade root and the disc, forcing the cooling air up through the blade root into the airfoil portion of the turbine blade. The cooling air thereafter exits from the airfoil portion into the exhaust path of the hot motive gases. The sealing assembly of the latter patent comprises a seal structure mating with grooves within the blade root and the disc to close the exhaust end of the cooling path between the blade root and the disc. Hence, use of the apparatus described in the latter patent requires special machining of the rotor disc as well as a specially structured tur-bine blade.
While the sealing assembly described above provides an efficient and effective method for channeling cooling air to the turbine bLade, it is not readily adapt-able to combustion turbines presently in the field.Application of this structure to field units would re~uire structura' ~odifications to both the turbine blade root 71!~
3 49,59~
and the rotor disc. Modification to the rotor disc T~ould necessitate removal of the rotor spindle from the lower half of the turbine casiny. As explained in U.S. Patent No. 3,493,212, the positioning of the rotor is highly critical, so that once it is properly located it should remain undist-lrbed if at all possible. Removal of the rotor splndle also increases the time and expense required to implement changes to the combustion turbine.
Hence, it would be advantageous to develop a cooled combustion turbine blade with sealing structure such that it may be backfitted into presently existing rotor discs, thereby providing the advantages of cooled turbine blades without the disadvantages of rotor spindle removal.
SUMMARY OF THE INV~NTION
Accordingly, a combustion turbine rotor blade which has a cooling system and sealing apparatus and is adapted for support on a rotor disc is provided for re-placing non-cooled turbine blades in presently existiny combustion turbines. The turbine blade, with cooling system and sealing apparatus, operates in cooperation with the rotor disc to effect a blade cooling structure in presently existing discs having non-cooled blades. The cooling system comprises means within a blade airfoil and a blade root for conducting coolant fluid therethrough.
The sealing apparatus is structured to affix to the blade root and sealingly close an axially extending chamber formed between the radially innermost portion of the blade root and the rotor disc. The sealing apparatus thereby closes a former exhaust path for coolant fluid and forces the coolant fluid into the turbine blade. Use of the cooled turbine blade requires no modification or disassem-bly of the turbine rotor assembly.
BRIEF D~SCRIPTION OF T~E DRAWINGS
Figure 1 shows a section ~iew of a portion of a typical prior art turbine section of a combustion turbine.
~7~
a 4~, 596 ~ igure 2 shows a section view of a portion of a -turbine bla~e wit~. sealing apparatus and cooLiny system structured according to the principles of the invention.
Figure 3 shows a front perspective vie~" of the sealing apparatus of the invention.
Figure 4 shows a side view of the sealing appar-atus of the invention.
Figure 5 shows a cutaway of Figure 2 in section revealing an upstream view of the cooled turbine blade root and sealing apparatus of the invention in position within the turbine disc.
DESCRIPTION ~F THE PREFERRED EMBODIMENT
Increased combustion turbine operating tempera-tures in presently existing combustion turbines has made it necessary to provide cooled turbine blades where before the blades were not cooled. In accordance with the prin-ciples of the invention, a combustion turbine blade with cooling system and sealing apparatus is provided. The blade is adapted ~or support on and operates in coopera-tion with prior art turbine rotor discs, providing a bladecooling structure for presently operating turbines having discs with non-cooled blades. The cooled turbine blade comprises a turbine blade specially constructed for con-duction of cooling fluid and a sealing apparatus for closing a fluid flow path between the blade root and the disc of the prior art structure and thereby forcing cool-ant 1uid to flow within the modified turbine blade struc-ture.
Referring now to the drawings, Eigure l shows a portion of a typical prior art rotor lO for an axial flow turbine in longitudinal section. The rotor lO may com-prise an aggregate of rotor discs only ~wo of which 12, 14 are shown, secured together by circumferentially disposed tie or staybolts 15 e~tending through the discs, only one tie bolt being shown in Figure l.
The discs 12, ].4 support, respectively, rotor bl-~des 16, 18 extending radially outwardly therefrom, the 8~
~9,596 blades bein~ d sposed between axialLy spaced, in~Jardiy extending fixed stator or nozzle blades 20, 21, 22. The rotor blades arG respectively provided with root portions 26, 28 of the side entry type which may be of the serrated or "fur tree" type for disposition in serrated recesses (see Fig. 5) provided in the periphery of the discs.
The rotor discs 12, 14 are further provided respectively with axially extending openings or channels 30, 32. The channels are in fluid communication with a passageway 33 formed by a tubular fairing member 34 dis-posed in encompassing relation with a center torque tube structure 35.
The discs 12, 14 are provided with circumfer-entially spaced, radially extending openings 40 on the upstream side and near the pariphery thereof. The open-ings 40 are formed in the disc to be in fluid communi-cation with the passa~eway 33.
The upstream side of the disc 12, 14 is further provided with an annular, continuous groove or channel 42 facing in a radially outward direction. The groove is formed in fluid communication with the radially extending openings 40. The detail of this typical prior art struc-ture is further described in U.S. ~atent No. 3,572,966.
Figure 2 shows a portion of the prior art disc 12 with a turbine blade and sealing mechanism structured accordin~ to the principles of the invention. For the purposes of the invention, the structure of disc 12 and disc 14 are substantially identical. The turbine blade 16 compri.ses an airfoil portion 46 and a root portion 26.
The root portion of the turbine blade is secured to the disc by the serrated structure of the blade~disc juncture and by conventional sideplates 48, 50, such as those described in U.S. Patent No. 3,572,966. The annularly disposed upstream sideplates 50, when secured within grooves 52, 54 formed respectively in the disc and blade define a continuous circumferential coolant chamber 4 with the adjacent ends of the roots 26 of the turbine ~8~7~
6 49,596 blades. The coolant chamber 44 is structured in ~luid communication with the continuous channel 42 and the radial openings 40.
In operation of the rotor a pressurized coollng fluid such as air from a compressor section of the com-bustion turbine is directed through the passageway 33 to the first disc 12 (see Figure 1). At the disc 12, the flow of air divides, part of the air traveling through the axial opening 30 in the disc 12 to the second disc 14.
The remainder of the air is directed radi~lly outward (upward in Figure 1 as indicated by the appropriats ar-rows) to the openings 40 beneath the annular groove 42.
From the annular groove 42 the air is then directed into the annular chamber 44 formed by the upstream sideplates and the ends of the blade roots. The flow of air is then directed through the clearances between the blade root and disc recesses and particularly into a plenum chamber 56 formed between the base of the blade root and the turbine disc.
In the typical prior art structure of Figure 1 the cooling air would pass from the plenum chamber 56 through an aperture in the exhaust sideplate 48 and into the e~haust path of the hot motive gases driving the turbine. In the cooling mechanism of the invention, a sealing apparatus 58, shown in greater detail in Figures 3, 4, and 5, closes the exhaust end of the plenum chamber 58, forcing the cooling air into radially extending chan-nels 60 within the turbine blade. The precise arrangement for coolant flow within the root and airfoil portions of the turbine blade is not critical to an understanding of the principles of the invention and may be any of several arrangements well known in the prior art.
The sealing apparatus 58 is structured so as to require no structural modification of the rotor disc 12 for its implementation. Figure 3 shows an upstream per-spective view of the sealing apparatus 5t3 Figure 4 shows a side view OI the same sealing apparatus. The upper por 3'7~
7 49,5~6 tion of the sealing apparatus is shaped to fit continu-ously within the radially innermost serration ~4 (Fig. 5) of the root portion of the turbine blade. The upper portion 62 of the sealing apparatus also defines a rectan-gular notch 66 which permits fixed engagement of thesealing apparatus within the root of the turbine blade.
A lower portion 68 of the sealing apparatus 58 is shaped to fit closely the periphery 70 (Fig. 5) of the plenum chamber 56 so as to seal the downstream end of that chamber. The thickness of the lower portion should be sufficient to assure adequate sealing of the plenum cham-ber but should preferably be no greater than the radial dimens.ion of the lower portion. ~ recess 72 of any con-venient configuration is provided in the lower portion o the sealing apparatus in the face which is adjacent the exhaust sideplate 48. The recess 72 simplifies assembly and disassembly of the sealing apparatus within the blade root and plenum chamber.
The exhaust end of the bottom serration of the blade root is notched as shown in Figure 2 at 74 to permit the upper portion 62 of the sealing apparatus to fit closely within the disc serration. A blade tab 76 inte-gral with the blade root mates with the rectangular notch 66 in the upper portion of the sealing apparatus, re-stricting movement of the sealing apparatus in the axialdirection. The close fitting shape of the sealing appara-tus within the disc serration and plenum chamber restricts movement of the sealing apparatus in the radial direction.
Thus, the combination of a cooled turbine blade and a sealing apparatus, cooperating accordin~ to the principles of the invention, provides a simple and yet effective structure which may be backfitted into presently existing co~bustion turbines having non-cooled blades.
The turbine blade a~d its cooling mechanism set forth herein permit replacement of non-cooled turbine blades with cooled turbine blades without s ructural modification or disturbance of the turbine rotor.
Claims (5)
1. A cooled turbine blade assembly adapted for installation on a rotor disc 1) having axially extending serrated lots provided about the disc periphery to receive serrated blade root portions in mating engagement;
2) having means for providing a flow of cooling air through a plenum chamber in each blade root slot between the blade roots and the disc; and 3) otherwise being designed for use with non-cooled turbine blades said blade assembly comprising a blade having an airfoil portion and a root portion engageable with the disc in one of the recesses and means for conducting cooling fluid from the plenum chamber beneath the root portion through the root portion and the airfoil portion and into an exhaust path to the motive axial fluid surrounding the airfoil portion; and a down-stream end of said plenum chamber a separate sealing member having a first portion thereof engageable with said blade root portion and a second portion thereof disposable in the associated serrated disc slot to close off the plenum chamber on the blade downstream side, and side plate means for locking said blade and sealing member in place.
2) having means for providing a flow of cooling air through a plenum chamber in each blade root slot between the blade roots and the disc; and 3) otherwise being designed for use with non-cooled turbine blades said blade assembly comprising a blade having an airfoil portion and a root portion engageable with the disc in one of the recesses and means for conducting cooling fluid from the plenum chamber beneath the root portion through the root portion and the airfoil portion and into an exhaust path to the motive axial fluid surrounding the airfoil portion; and a down-stream end of said plenum chamber a separate sealing member having a first portion thereof engageable with said blade root portion and a second portion thereof disposable in the associated serrated disc slot to close off the plenum chamber on the blade downstream side, and side plate means for locking said blade and sealing member in place.
2. An apparatus according to claim 1 wherein said sealing member comprises:
an upper portion shaped to fit closely within a notched corner of a radially innermost serration of the blade root, so that the upper portion of said sealing means is generally continuous with the blade root; and a lower portion shaped in the radial plane to closely fit and fill the space between the walls of the plenum chamber and dimensioned in the axial plane to a thickness which is less than the radial dimension of the lower portion.
an upper portion shaped to fit closely within a notched corner of a radially innermost serration of the blade root, so that the upper portion of said sealing means is generally continuous with the blade root; and a lower portion shaped in the radial plane to closely fit and fill the space between the walls of the plenum chamber and dimensioned in the axial plane to a thickness which is less than the radial dimension of the lower portion.
3. An apparatus according to claim 2 wherein the upper portion of said sealing means is notched along both radial plane surfaces to mate with corresponding grooves in the blade root so as to stabilize the sealing means in the axial direction.
4. An apparatus according to claim 3 wherein said apparatus includes a mating tab integral with the blade root and interlocking with a corresponding notch in the radial plane surface of said sealing means facing away from the plenum chamber.
5. An apparatus according to claim 2 wherein the lower portion of said sealing means defines a recess extending from the radial plane surface facing away from the plenum chamber in the axial direction, the recess aiding in assembly and disassembly of said sealing means.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US30476081A | 1981-09-22 | 1981-09-22 | |
| US304,760 | 1989-01-31 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1187810A true CA1187810A (en) | 1985-05-28 |
Family
ID=23177893
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000410997A Expired CA1187810A (en) | 1981-09-22 | 1982-09-08 | Cooled combustion turbine blade with retrofit blade seal |
Country Status (2)
| Country | Link |
|---|---|
| JP (2) | JPS5865903A (en) |
| CA (1) | CA1187810A (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA1209482A (en) * | 1983-12-22 | 1986-08-12 | Douglas L. Kisling | Two stage rotor assembly with improved coolant flow |
| RU2548226C2 (en) * | 2010-12-09 | 2015-04-20 | Альстом Текнолоджи Лтд | Fluid medium flow unit, in particular, turbine with axially passing heated gas flow |
| IN2014DN08366A (en) * | 2012-05-08 | 2015-05-08 | Siemens Ag | |
| JP6125277B2 (en) * | 2013-02-28 | 2017-05-10 | 三菱重工業株式会社 | gas turbine |
-
1982
- 1982-09-08 CA CA000410997A patent/CA1187810A/en not_active Expired
- 1982-09-16 JP JP15973482A patent/JPS5865903A/en active Pending
-
1985
- 1985-11-21 JP JP1985178329U patent/JPS6343361Y2/ja not_active Expired
Also Published As
| Publication number | Publication date |
|---|---|
| JPS6199603U (en) | 1986-06-25 |
| JPS6343361Y2 (en) | 1988-11-11 |
| JPS5865903A (en) | 1983-04-19 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MKEC | Expiry (correction) | ||
| MKEX | Expiry |