CA2235153A1 - Variable area compensation valve - Google Patents
Variable area compensation valve Download PDFInfo
- Publication number
- CA2235153A1 CA2235153A1 CA 2235153 CA2235153A CA2235153A1 CA 2235153 A1 CA2235153 A1 CA 2235153A1 CA 2235153 CA2235153 CA 2235153 CA 2235153 A CA2235153 A CA 2235153A CA 2235153 A1 CA2235153 A1 CA 2235153A1
- Authority
- CA
- Canada
- Prior art keywords
- housing
- inlet
- valve
- pressure
- turbine engine
- 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.)
- Abandoned
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- Control Of Turbines (AREA)
Abstract
A variable area restrictor is disclosed that is preferably used in a turbine engine to provide improved matching between the pressure required for aerofoil cooling and the somewhat lower pressure requirement for supplying air to the interstage seals and disc cavities. In a preferred embodiment, the valve of the present invention comprises a spring loaded valve assembly with a fixed minimum flow area controlled by pre-setting a minimum dimension for the opening between an inlet and the housing or body of the valve. A pre-loaded spring maintains the lift at this minimum dimension until the pressure drop across the flow area exceeds a certain value. Above this critical pressure drop, the valve lifts, causing the flow area to increase, and thereby reducing the supply pressure that would be otherwise necessary to achieve a disc cavity flow adequate to maintain the temperatures within specifications.
Description
!U--'YYi li'~ 4 c~4~c~>~ CA 02235l53 l998-04-l6 ~ ~~~ Y-~4 WO ~7/1~871 PCr/l.,'Bg6/lf~2S
VA~ aL~ AR~A CC:MPENS~TION V~t7E
Tha present i:~rentiQ~ relato~ to tur~omac~$nery and in pa~t~ e~l~r to tur~ ne engin~3 . More pa~ticularly, the pre~er~' in~rant~cr~ r~ te3 to me~hod~ and apparatu~ o~
rogulating the ~iow o~ g~sea throush the t~r~ine b!ades - 5 th~miYei~re~ a~ es combu2ation.
~AC~n~OUN~ OF T~ IN~rrION
Th~ background o~ turbomachinery i~ well 3cnown in the a_t ~.d 'un~ liarl y with ouch art ~ 8 pre~umed. The detalls ~ a typ~cal Fr~ 5- ar: tu--bl~.e are disclosed in U. S .
0 P~tenl- 4, 863, 343, which 18 i~u~d to the in~en~or o~ the ~r~e~nt ~v~n~o~a a~d aa~l~ned to the ~ig~ o~ the Fr~ent ~ rention. ~o dll-closura of thi~ pateslt is ir.co~porato~
h~rein ry x~f~r~ce a~ $~ fully 9et fo~th .
It ~a recogniz~d i~ thc prior ar~ that ~arying turbine engin~ conditions require ~ary~ng c-oling flow t3 th~ hot tur~inc part~. Uni~ed States paten~ 3,452,~42 and ~K patent appli~a~ion~ 5~-~-2 170 ~ a~d GB-A-2 175 04~
te~ch ~r~ine ensines whic~ utilize valves ~o r-gulate the ~low of cooling ~1-. How~vQr, ~hese prior ar~ ~ystem~ rely ~~ on a variety ~f ~en~ore to meaGure turbine ope-ating conditic~ such ~ air temperature. ~peed, altitude, etc.
fo~ the active cont~ol o~ the air flo~ regulatir,g va' ve .
Such sy~teme a~e complic~ed and ex~ensi~e. Furthermcre, they make rlo dl~erenr iation between cooling re~uirement5 ' S f or dlf~erent pcrtion~ o~ the ~urbine.
AI~ENDED SHEET
_ li--~J~S--~ L' ~ b4~c~b~ .N;tL~=_lU~_L ~I~U~
WO 9~ 6/1 ~2 la Typical prior ~rt turb$n-- u~ a ~lx~d, l-ow reJtrlctio~s flo~ ar~ th~r ~kroud ~o aupply a~ ~ tO t~le and ~c c~v~ t~omc dcslg~s, howcv-r, th~
prc-Jur- rc~uls-d ~'~r ~tat~r ~n~ cooling i~ con-ldera~ly 5 hl~r th~ ehae roc~u~r~d ~o~ ~hc ~eal~ d ~l~c cavle i e~
~h ~ eh~ tuaclo;l ~c~ur~ thc p~o~Jurc mu~t ~e raised ~o-~~h~ van~ ~nd ~ th~o~oro hig~L~s ~--n ~u' red for di~c ca~riey ~low- th-r-by r-~ult~ng ~n ~x~ v~ ~akag~ T~ cha~ge~ i~
om~ by r-duc-d en~in- per~o. ~nc- wkich muee be ~o~ d o~ t~on-l cc.~r~eing pro~Ju-c d~op m~t be nto th~ t~m at th~ sou ~y dacr~a~ng th~
othorwlJ- r~l-t~v-ly la~ r ~hroud f low ~r-a . E~ow-v~r, th~ c~ors at th~ hrcud ~ho~'d ~ acc~peable f~s ~ C cp-r~lon. A p~obl-~ ar~s if ~h-15 ~l~C C~Y1ty i!1o~ r~ r~d co m~ine~i~ ac~-p~ y low AhJ~ENDED SHEET
~ CA 0223~1~3 1998-04-16 Wo97114871 PCT~S96/14425 cavity temperatures is higher than expected. Should this situation arise in an assembled, ready to run engine, the only choice i8 to increase the pressure at the outer vane shroud until sufficient inner shroud flow and acceptably low disc cavity temperatures are obtained. As a result, the outer shroud pressure is now higher than required for vane cooling and preventing contamination, and hence a potentially large additional performance-penalizing flow will be automatically supplied from the compressor bleed system, in addition to what is actually required for the disc cavities.
Therefore, it would be desirable to provide an apparatus and methods by which the pressure required for airfoil cooling in a turbine can be achieved without jeopardizing the lower pressure requirement for supplying air ~ 15 to the interstage seals and disc cavities. Accordingly, it is an object of the present invention to permit the compensation of the pressure within various sections of a turbine engine. It is a further object o~ the present invention to optimize the pressure distribution within a turbine so as to achieve maximum efficiency and maximize power.
SUMMARY OF THE INVENTION
It has now been found that the above-described problem can be minimized and thè above-state objectives 2S achieved by inserting a variable area restrictor at the inner shroud in place of the otherwise fixed geometry flow area.-The present invention provides a variable area matching valve de~igned to provide ~or improved matching between the pressure required for aerofoil cooling and the lower pressure requirement for supplying air to the interstage seals and disc cavities. In a pre~erred embodiment, the variable area valve of the present invention comprises a spring-loaded valve assembly with a fixed minimum flow area controlled by pre-setting a minimum dimension for the opening between an inlet and the housing or body of the valve. A pre-loaded spring maintains the lift at this minimum dimension until the pressure drop across the flow area exceeds a certain value.
CA 0223~l~3 l998-04-l6 Wo 97/14871 PCT/US96/14425 Above this critical pressure drop, the valve lifts, causing the flow area to increase, and thereby reduce the supply pressure that would be otherwise necessary to achieve a disc cavity flow adequate to maintain the operating temperatures 5 within specification.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is cross-sectional view of the variable area compensation valve of the present invention and the ~ surrounding components of a typical turbine engine;
10FIG. 2 is a cross-sectional taken along section line A-A in FIG. 1 to illustrate the typical shape of the inlet and the distal end of the variable area compensation valve of the present invention; and FIG. 3 is a cross-sectional view of FIG. 2 taken 15along line B-B to illustrate the structure of a preferred embodiment of the restriction section of the variable area compensation valve of the present invention.
DETAILED DESCRIPTION OF THE INVENTION
The present invention is designed to provide 20improved matching between the pressure required for air flow cooling and the lower pressure re~uired for supplying air to the interstage seals and disc cavities. As mentioned above, a ~ixed, low restriction flow area at the inner shroud is typically used to supply air to the seals and disc cavities.
25A preferred embodiment of a variable area compensation valve which m;n;m; zes the above-described problems by inserting a variable area restrictor at the inner shroud in place of the otherwise fixed geometry flow area is illustrated in FIG. 1.
Referring now to FIG. 1, a preferred embodiment of 30a variable area restrictor 100 is shown positioned between an inlet 52 and an outlet 54 in a gas flow system such as that found within a turbine engine 50. The variable area restrictor 100 preferably comprises a housing 120 connected t to the inlet 52. The housing 120 preferably has a housing 35port or ports 122 in communication with the outlet 54. The variable area restrictor 100 also has an adjustable inner section 104 connected to the housing 120, and a piston 106 CA 0223~l~3 l998-04-l6 WO97/14871 PCT~S96/14425 disposed around the inner section 104 and in sliding engagement therewith. The piston 106 has a distal end 116 disposed a variable distance (CmLn) between the inlet 52 and the housing 120. In preferred embodiments, the inner section 104 is threaded and cooperates with threads on the housing 120. By rotating the inner section 104, the distance the piston 106 can travel is adjusted, and the variable distance, CmLn~ can be altered. A spring 108 is preferably disposed between the piston 106 and the inner section 104 such that the distal end of the piston 116 is urged toward a position that would close off the inlet 52.
As seen in FIG. 2, the housing 120 is connected to the turbine 50 by one or more standoffs 110. Also visible in FIG. 2 is a preferred shape of the opening that communicates with the inlet 52. In a preferred embodiment, the distal end of the piston 106 comprises a raised, non-circular ridge 126 for defining a passage between the inlet 52 and the housing 120. As illustrated, distances l1 and 12 define the relationship between these areas. Further details of these aspects of the invention are illustrated in FIG. 3, which shows an enlarged and broken away view of the non-circular ridge 126 and its relationship to the distance Cmin described above.
Thus, when the disclosed valve structure 100 is in operation and the pressure drop at the inlet 52 reaches a pre-determ;ne~ level, the piston 116 moves against the biasing force of the spring 108 and creates a greater area, i.e., the distance Cmin increases, thereby reducing the pressure and increasing the flow. The spring-loaded valve assembly 100 with a fixed minimum flow area is controlled by pre-setting a minimum clearance distance (Cmin) via the local standoffs 110 seen in FIG. 2. The pre-loaded spring 108 maintains a lift at Cmin until the pressure drop (P1-P2) across the flow area is established by the Cmin exceeds a certain, pre-determined critical pressure drop value. Above this critical pressure drop, the piston 106 of the valve loO lifts, causing the flow area to increase, thereby reducing the supply pressure that CA 0223~1~3 1998-04-16 Wo97/14871 PCT~S96/14425 would otherwise be necessary to achieve a disc cavity flow adequate to maintain the disc cavity temperature within specifications.
The present invention thus provides a variable area orifice for a combustion turbine at the stator vane in a shroud which provides additional cooling ~10w without a commensurate increase in supply pressure. More generally, a variable area restrictor positioned between an inlet and an outlet in a gas flow system is disclosed which includes a housing connected to the inlet that has a port in communication with the outlet. A piston disposed between the inlet and the housing port permits the area between the inlet and the outlet, i.e., a restriction, to vary so that when the pressure at the inlet reaches a pre-determined level, the ~ 15 piston moves and creates a greater area, thereby reducing the pressure and increasing the flow.
Although certain embodiments of the present invention have been set forth above and described in detail, these embodiments are meant to be descriptive and the present invention is not to be limited by this disclosure. Upon reviewing the foregoing description, those of skill in the art will immediately realize various improvements, modifications and adaptation of the concepts disclosed herein without departing from the spirit of the present invention. For example, there are numerous types of variable restrictors that are generally known that can be adapted for use with the concepts disclosed herein. Alternatively, the variable restriction valve structure disclosed herein can be readily incorporated into other flow systems in addition to the specific example of a turbine that is provided above.
Therefore, reference should be made to the appended claims in order to determine the full scope of the present invention.
VA~ aL~ AR~A CC:MPENS~TION V~t7E
Tha present i:~rentiQ~ relato~ to tur~omac~$nery and in pa~t~ e~l~r to tur~ ne engin~3 . More pa~ticularly, the pre~er~' in~rant~cr~ r~ te3 to me~hod~ and apparatu~ o~
rogulating the ~iow o~ g~sea throush the t~r~ine b!ades - 5 th~miYei~re~ a~ es combu2ation.
~AC~n~OUN~ OF T~ IN~rrION
Th~ background o~ turbomachinery i~ well 3cnown in the a_t ~.d 'un~ liarl y with ouch art ~ 8 pre~umed. The detalls ~ a typ~cal Fr~ 5- ar: tu--bl~.e are disclosed in U. S .
0 P~tenl- 4, 863, 343, which 18 i~u~d to the in~en~or o~ the ~r~e~nt ~v~n~o~a a~d aa~l~ned to the ~ig~ o~ the Fr~ent ~ rention. ~o dll-closura of thi~ pateslt is ir.co~porato~
h~rein ry x~f~r~ce a~ $~ fully 9et fo~th .
It ~a recogniz~d i~ thc prior ar~ that ~arying turbine engin~ conditions require ~ary~ng c-oling flow t3 th~ hot tur~inc part~. Uni~ed States paten~ 3,452,~42 and ~K patent appli~a~ion~ 5~-~-2 170 ~ a~d GB-A-2 175 04~
te~ch ~r~ine ensines whic~ utilize valves ~o r-gulate the ~low of cooling ~1-. How~vQr, ~hese prior ar~ ~ystem~ rely ~~ on a variety ~f ~en~ore to meaGure turbine ope-ating conditic~ such ~ air temperature. ~peed, altitude, etc.
fo~ the active cont~ol o~ the air flo~ regulatir,g va' ve .
Such sy~teme a~e complic~ed and ex~ensi~e. Furthermcre, they make rlo dl~erenr iation between cooling re~uirement5 ' S f or dlf~erent pcrtion~ o~ the ~urbine.
AI~ENDED SHEET
_ li--~J~S--~ L' ~ b4~c~b~ .N;tL~=_lU~_L ~I~U~
WO 9~ 6/1 ~2 la Typical prior ~rt turb$n-- u~ a ~lx~d, l-ow reJtrlctio~s flo~ ar~ th~r ~kroud ~o aupply a~ ~ tO t~le and ~c c~v~ t~omc dcslg~s, howcv-r, th~
prc-Jur- rc~uls-d ~'~r ~tat~r ~n~ cooling i~ con-ldera~ly 5 hl~r th~ ehae roc~u~r~d ~o~ ~hc ~eal~ d ~l~c cavle i e~
~h ~ eh~ tuaclo;l ~c~ur~ thc p~o~Jurc mu~t ~e raised ~o-~~h~ van~ ~nd ~ th~o~oro hig~L~s ~--n ~u' red for di~c ca~riey ~low- th-r-by r-~ult~ng ~n ~x~ v~ ~akag~ T~ cha~ge~ i~
om~ by r-duc-d en~in- per~o. ~nc- wkich muee be ~o~ d o~ t~on-l cc.~r~eing pro~Ju-c d~op m~t be nto th~ t~m at th~ sou ~y dacr~a~ng th~
othorwlJ- r~l-t~v-ly la~ r ~hroud f low ~r-a . E~ow-v~r, th~ c~ors at th~ hrcud ~ho~'d ~ acc~peable f~s ~ C cp-r~lon. A p~obl-~ ar~s if ~h-15 ~l~C C~Y1ty i!1o~ r~ r~d co m~ine~i~ ac~-p~ y low AhJ~ENDED SHEET
~ CA 0223~1~3 1998-04-16 Wo97114871 PCT~S96/14425 cavity temperatures is higher than expected. Should this situation arise in an assembled, ready to run engine, the only choice i8 to increase the pressure at the outer vane shroud until sufficient inner shroud flow and acceptably low disc cavity temperatures are obtained. As a result, the outer shroud pressure is now higher than required for vane cooling and preventing contamination, and hence a potentially large additional performance-penalizing flow will be automatically supplied from the compressor bleed system, in addition to what is actually required for the disc cavities.
Therefore, it would be desirable to provide an apparatus and methods by which the pressure required for airfoil cooling in a turbine can be achieved without jeopardizing the lower pressure requirement for supplying air ~ 15 to the interstage seals and disc cavities. Accordingly, it is an object of the present invention to permit the compensation of the pressure within various sections of a turbine engine. It is a further object o~ the present invention to optimize the pressure distribution within a turbine so as to achieve maximum efficiency and maximize power.
SUMMARY OF THE INVENTION
It has now been found that the above-described problem can be minimized and thè above-state objectives 2S achieved by inserting a variable area restrictor at the inner shroud in place of the otherwise fixed geometry flow area.-The present invention provides a variable area matching valve de~igned to provide ~or improved matching between the pressure required for aerofoil cooling and the lower pressure requirement for supplying air to the interstage seals and disc cavities. In a pre~erred embodiment, the variable area valve of the present invention comprises a spring-loaded valve assembly with a fixed minimum flow area controlled by pre-setting a minimum dimension for the opening between an inlet and the housing or body of the valve. A pre-loaded spring maintains the lift at this minimum dimension until the pressure drop across the flow area exceeds a certain value.
CA 0223~l~3 l998-04-l6 Wo 97/14871 PCT/US96/14425 Above this critical pressure drop, the valve lifts, causing the flow area to increase, and thereby reduce the supply pressure that would be otherwise necessary to achieve a disc cavity flow adequate to maintain the operating temperatures 5 within specification.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is cross-sectional view of the variable area compensation valve of the present invention and the ~ surrounding components of a typical turbine engine;
10FIG. 2 is a cross-sectional taken along section line A-A in FIG. 1 to illustrate the typical shape of the inlet and the distal end of the variable area compensation valve of the present invention; and FIG. 3 is a cross-sectional view of FIG. 2 taken 15along line B-B to illustrate the structure of a preferred embodiment of the restriction section of the variable area compensation valve of the present invention.
DETAILED DESCRIPTION OF THE INVENTION
The present invention is designed to provide 20improved matching between the pressure required for air flow cooling and the lower pressure re~uired for supplying air to the interstage seals and disc cavities. As mentioned above, a ~ixed, low restriction flow area at the inner shroud is typically used to supply air to the seals and disc cavities.
25A preferred embodiment of a variable area compensation valve which m;n;m; zes the above-described problems by inserting a variable area restrictor at the inner shroud in place of the otherwise fixed geometry flow area is illustrated in FIG. 1.
Referring now to FIG. 1, a preferred embodiment of 30a variable area restrictor 100 is shown positioned between an inlet 52 and an outlet 54 in a gas flow system such as that found within a turbine engine 50. The variable area restrictor 100 preferably comprises a housing 120 connected t to the inlet 52. The housing 120 preferably has a housing 35port or ports 122 in communication with the outlet 54. The variable area restrictor 100 also has an adjustable inner section 104 connected to the housing 120, and a piston 106 CA 0223~l~3 l998-04-l6 WO97/14871 PCT~S96/14425 disposed around the inner section 104 and in sliding engagement therewith. The piston 106 has a distal end 116 disposed a variable distance (CmLn) between the inlet 52 and the housing 120. In preferred embodiments, the inner section 104 is threaded and cooperates with threads on the housing 120. By rotating the inner section 104, the distance the piston 106 can travel is adjusted, and the variable distance, CmLn~ can be altered. A spring 108 is preferably disposed between the piston 106 and the inner section 104 such that the distal end of the piston 116 is urged toward a position that would close off the inlet 52.
As seen in FIG. 2, the housing 120 is connected to the turbine 50 by one or more standoffs 110. Also visible in FIG. 2 is a preferred shape of the opening that communicates with the inlet 52. In a preferred embodiment, the distal end of the piston 106 comprises a raised, non-circular ridge 126 for defining a passage between the inlet 52 and the housing 120. As illustrated, distances l1 and 12 define the relationship between these areas. Further details of these aspects of the invention are illustrated in FIG. 3, which shows an enlarged and broken away view of the non-circular ridge 126 and its relationship to the distance Cmin described above.
Thus, when the disclosed valve structure 100 is in operation and the pressure drop at the inlet 52 reaches a pre-determ;ne~ level, the piston 116 moves against the biasing force of the spring 108 and creates a greater area, i.e., the distance Cmin increases, thereby reducing the pressure and increasing the flow. The spring-loaded valve assembly 100 with a fixed minimum flow area is controlled by pre-setting a minimum clearance distance (Cmin) via the local standoffs 110 seen in FIG. 2. The pre-loaded spring 108 maintains a lift at Cmin until the pressure drop (P1-P2) across the flow area is established by the Cmin exceeds a certain, pre-determined critical pressure drop value. Above this critical pressure drop, the piston 106 of the valve loO lifts, causing the flow area to increase, thereby reducing the supply pressure that CA 0223~1~3 1998-04-16 Wo97/14871 PCT~S96/14425 would otherwise be necessary to achieve a disc cavity flow adequate to maintain the disc cavity temperature within specifications.
The present invention thus provides a variable area orifice for a combustion turbine at the stator vane in a shroud which provides additional cooling ~10w without a commensurate increase in supply pressure. More generally, a variable area restrictor positioned between an inlet and an outlet in a gas flow system is disclosed which includes a housing connected to the inlet that has a port in communication with the outlet. A piston disposed between the inlet and the housing port permits the area between the inlet and the outlet, i.e., a restriction, to vary so that when the pressure at the inlet reaches a pre-determined level, the ~ 15 piston moves and creates a greater area, thereby reducing the pressure and increasing the flow.
Although certain embodiments of the present invention have been set forth above and described in detail, these embodiments are meant to be descriptive and the present invention is not to be limited by this disclosure. Upon reviewing the foregoing description, those of skill in the art will immediately realize various improvements, modifications and adaptation of the concepts disclosed herein without departing from the spirit of the present invention. For example, there are numerous types of variable restrictors that are generally known that can be adapted for use with the concepts disclosed herein. Alternatively, the variable restriction valve structure disclosed herein can be readily incorporated into other flow systems in addition to the specific example of a turbine that is provided above.
Therefore, reference should be made to the appended claims in order to determine the full scope of the present invention.
Claims (5)
1. A turbine engine (50) having a variable area restrictor (100) at the stator vane inner shroud for supplying cooling air, said inner shroud having an inlet (52) and outlet (54), characterized by:
a housing (120) connected to the inlet (52), the housing (120) having a housing port (122) in communication with the outlet (54);
an adjustable inner section (104) connected to the housing (120);
a piston (106) disposed around the inner section (104) and having a distal end (116) disposed a variable distance between the inlet (54) and the housing (120); and a spring (108) disposed between the piston (106) and the inner section (104), whereby when the pressure at the inlet (52) reaches a predetermined level, the piston (106) moves and creates a greater area, thereby reducing the pressure and increasing the flow of said cooling air.
a housing (120) connected to the inlet (52), the housing (120) having a housing port (122) in communication with the outlet (54);
an adjustable inner section (104) connected to the housing (120);
a piston (106) disposed around the inner section (104) and having a distal end (116) disposed a variable distance between the inlet (54) and the housing (120); and a spring (108) disposed between the piston (106) and the inner section (104), whereby when the pressure at the inlet (52) reaches a predetermined level, the piston (106) moves and creates a greater area, thereby reducing the pressure and increasing the flow of said cooling air.
2. The turbine engine (50) of claim 1, further characterized by the inner section (104) being threaded to cooperate with threads on the housing (120).
3. The turbine engine (50) of claim 1, further characterized by the housing (120) being connected to the inlet (52) by one or more standoffs (110).
4. The turbine engine (50) of claim 1, further characterized by distal end of the piston (110) having a raised, non-circular ridge (126) for defining a passage between the inlet (52) and the housing (120).
5. The turbine engine (50) of claim 2, further characterized by said variable distance being altered by rotating said inner section (104).
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US08/544,348 | 1995-10-17 | ||
| US08/544,348 US5636659A (en) | 1995-10-17 | 1995-10-17 | Variable area compensation valve |
| PCT/US1996/014425 WO1997014871A1 (en) | 1995-10-17 | 1996-09-05 | Variable area compensation valve |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA2235153A1 true CA2235153A1 (en) | 1997-04-24 |
Family
ID=29405936
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA 2235153 Abandoned CA2235153A1 (en) | 1995-10-17 | 1996-09-05 | Variable area compensation valve |
Country Status (1)
| Country | Link |
|---|---|
| CA (1) | CA2235153A1 (en) |
-
1996
- 1996-09-05 CA CA 2235153 patent/CA2235153A1/en not_active Abandoned
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| FZDE | Dead |