CA1331100C - Device for keeping the annular outlet mouth of the gas volute always centered about the nozzle assembly in a gas turbine - Google Patents
Device for keeping the annular outlet mouth of the gas volute always centered about the nozzle assembly in a gas turbineInfo
- Publication number
- CA1331100C CA1331100C CA000596600A CA596600A CA1331100C CA 1331100 C CA1331100 C CA 1331100C CA 000596600 A CA000596600 A CA 000596600A CA 596600 A CA596600 A CA 596600A CA 1331100 C CA1331100 C CA 1331100C
- Authority
- CA
- Canada
- Prior art keywords
- ring
- volute
- retaining
- gas
- annular
- 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 - Fee Related
Links
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 20
- 238000002485 combustion reaction Methods 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000002159 abnormal effect Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/60—Support structures; Attaching or mounting means
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Control Of Turbines (AREA)
Abstract
DEVICE FOR KEEPING THE ANNULAR OUTLET MOUTH OF THE GAS VOLUTE
ALWAYS CENTERED ABOUT THE NOZZLE ASSEMBLY IN A GAS TURBINE
Abstract A device for keeping the annular outlet mouth of the gas volute always centered about the nozzle assembly in a gas turbine, consisting of two retaining half-rings embracing said annular mouth, the lower half-ring having an inner radius greater than that of the upper half-ring, this latter forming a predetermined gap with said annular mouth.
ALWAYS CENTERED ABOUT THE NOZZLE ASSEMBLY IN A GAS TURBINE
Abstract A device for keeping the annular outlet mouth of the gas volute always centered about the nozzle assembly in a gas turbine, consisting of two retaining half-rings embracing said annular mouth, the lower half-ring having an inner radius greater than that of the upper half-ring, this latter forming a predetermined gap with said annular mouth.
Description
~ 3 3 ~ ~ ~
DBVICE EOR KE~PI~G THE A~DULAR OUTLET MOUT~ OF THE GAS VOLUTE
ALWAYS CEJTERED ABOUT T~E ~OZZLE ASSEMBLY I~ A GAS T~R3I~E
This inventlou relates to a device which enables the annular outlet mouth oi' the gas volute to be kept always centered about the nozzle asse~bly even in gas turbines of h~gh co~pression ratlo and high flre temperature in which high loads act on the volute.
In all gas turblnes provlded with a slngle co~bustion chamber there is a volute the functicn oi wh$ch ls to dlstribute tbe hot gases i'ron the combustlon chamber ~nnularly to the array of nazzles.
As the volute, together with the combustion chamber walls, represents the hottest part of the turblne lt must necessarlly be oi the llghtest posslble sheet metal constructlon to limit thermal -~
stresse~ to a mi~it~tt~ with the result that it is unable to withstand hlgh locali~ed loads.
Again, the connection between the annular outlet uth of the ;~
volute and the nozzle support oannot be rigid because as their ~asses are different and they operate under different working 2~ conditions, these two members assume very different temperatures with consequent considerable dif~erential expausion. -There is therefore the problem of keeping the annular outlet uth -` ~33~
of the volute centered about the array of nozzles, and ensuring that lt is so, because any misalignment results in loss of turbine efflciency due to the sharp steps created in the gas passage duct.
The volute is sub~ected to mechanical loads deriving from lts welght (generally negligible) and in partlcular from the gas pressure and overall motlon differences between the lnlet and outlet. These mechanical loads, which beco~e greater the hlgher the turblne worklng pressures and thus the higher its compression ratio, create an upward force which moves the annular outlet mouth of the volute upwards.
In the current state of the art the classical system usually used to gutde said move~ent and to keep any two parts sub~ected to conslderable differentlal e~panslon concentric with each oth~r ls to connect said parts together by a set of radial keys which make it possible for the two parts to undergo relatlve slidlng whlle remalning concentric.
Such a method cannot however be applied to gas turbines of high compression ratlo and hlgh fire temperature because the consequent considerable loads actlng on the volute would have to be transmitted through said radial keys and specifically through only those keys in a horizontal plane, and this load concentratlon at the keys would lnduce intolerable stress states ln the volute which as stated has to be of very ll~ht constructlon because of the high gas temperature. - . ;
The ob~ect of the present inventlon ls to obviate sald drawback by provlding a device for connecting the annular outlet mouth of the volute to the nozzle support whlch although dlspenslng with the ~l331~
DBVICE EOR KE~PI~G THE A~DULAR OUTLET MOUT~ OF THE GAS VOLUTE
ALWAYS CEJTERED ABOUT T~E ~OZZLE ASSEMBLY I~ A GAS T~R3I~E
This inventlou relates to a device which enables the annular outlet mouth oi' the gas volute to be kept always centered about the nozzle asse~bly even in gas turbines of h~gh co~pression ratlo and high flre temperature in which high loads act on the volute.
In all gas turblnes provlded with a slngle co~bustion chamber there is a volute the functicn oi wh$ch ls to dlstribute tbe hot gases i'ron the combustlon chamber ~nnularly to the array of nazzles.
As the volute, together with the combustion chamber walls, represents the hottest part of the turblne lt must necessarlly be oi the llghtest posslble sheet metal constructlon to limit thermal -~
stresse~ to a mi~it~tt~ with the result that it is unable to withstand hlgh locali~ed loads.
Again, the connection between the annular outlet uth of the ;~
volute and the nozzle support oannot be rigid because as their ~asses are different and they operate under different working 2~ conditions, these two members assume very different temperatures with consequent considerable dif~erential expausion. -There is therefore the problem of keeping the annular outlet uth -` ~33~
of the volute centered about the array of nozzles, and ensuring that lt is so, because any misalignment results in loss of turbine efflciency due to the sharp steps created in the gas passage duct.
The volute is sub~ected to mechanical loads deriving from lts welght (generally negligible) and in partlcular from the gas pressure and overall motlon differences between the lnlet and outlet. These mechanical loads, which beco~e greater the hlgher the turblne worklng pressures and thus the higher its compression ratio, create an upward force which moves the annular outlet mouth of the volute upwards.
In the current state of the art the classical system usually used to gutde said move~ent and to keep any two parts sub~ected to conslderable differentlal e~panslon concentric with each oth~r ls to connect said parts together by a set of radial keys which make it possible for the two parts to undergo relatlve slidlng whlle remalning concentric.
Such a method cannot however be applied to gas turbines of high compression ratlo and hlgh fire temperature because the consequent considerable loads actlng on the volute would have to be transmitted through said radial keys and specifically through only those keys in a horizontal plane, and this load concentratlon at the keys would lnduce intolerable stress states ln the volute which as stated has to be of very ll~ht constructlon because of the high gas temperature. - . ;
The ob~ect of the present inventlon ls to obviate sald drawback by provlding a device for connecting the annular outlet mouth of the volute to the nozzle support whlch although dlspenslng with the ~l331~
- 3 - :
use of keys enables effective centering to be maintained, -~:~
even in gas turbines of high compressin ratio.
According to the present invention there is provided a device for keeping an annular outlet mouth of a gas volute :~
always centered about a nozzle assembly in a gas turbine, :
characterised by comprising two retaining half-rings, a lower half-ring and an upper half-ring, which are fixed to a nozzel support ring to embrace said annular mouth, the lower half-ring having an inner radius greater than that of the upper half-ring, which forms with an outer flange of said annular outlet mouth of the volute a predetermined gap arranged to compensate a differential expansion between said annular mouth and said nozzle support ring.
According to the present invention there is also provided a device for centering an annular outlet mouth of a gas volute relative to a nozzle assembly in a gas turbine wherein the nozzle assembly has a nozzle support ring surrounding the annular outlet mouth, comprising~
a) a first retaining diametrically divided ring attached to the nozzle support ring, wherein said first retaining ~ ~
ring has an outer radius and an inner radius; and -:
b) a second retaining diametrically divided ring attached to the nozzle support ring, wherein said second retaining ring has an outer radius and an inner radius, wherein said ~ :
outer radius of said second retaining ring is equal to said~ :~
outer radius of said first retaining ring and said inner -radius of said second retaining ring is greater than said :~
inner radius of said first retaining ring thereby forming a gap wherein said gap is effective to compensate for~:
differential expansion between the annular outlet mouth and :
the nozzle support ring.
, ,~ . .
~ 3 3 :~`
The invention is described in detail hereinafter with reference to the accompanying drawings which illustrate a preferred embodiment thereof given by way of non-limiting example in that technical or constructional modifications can be made thereto but without leaving the scope of the present invention.
In said drawings:
:
Fig. 1 is partial lateral section through a gas turbine using the device of the invention;
, Fig. la is an enlarged detail drawing showing the gap 14 shown in Fig. l;
Fig. lb is an enlarged detail drawing showing the gap 15 shown in Fig. l;
Fig. 2 is a partial front section on the line A-A of Fig. 1.
~ ' In the figures, the reference numeral 1 indicates a gas turbine casing which on bearings 2 rotatably supports the shaft 3 carrying the discs 4 of the turbine blades 5. Line 3a is the centerline of the shaft 3. The combustion chamber 6 is connected to a gas volute 7 the annular outlet mouth 8 of which faces the zone comprising the nozzles 9, which are supported radially by a nozzle support ring 10 supported by the turbine casing 1.
In order to keep the annular outlet mouth 8 always centered about the nozzle assembly 9, two retaining diametrically divided half-rings 12 and 13 are fixed above and below of the centerline 3a of the shaft 3 on the nozzle support ring 10 by bolts 11 to embrace said annular mouth 8 in such a ., ~ ........................................ ..
.. - '.', .
~ ~ 3 ~
manner as to leave a predetermined gap 14 between the upper half-ring 12 and the outer flange 7' of said annular outlet mouth 8. In addition, ~he lower half-ring 13 has a larger inner radius than the upper half-ring 12 (see Fig. 2 specifically), so that a greater empty space 15 is available.
:
The present invention thus keeps the annular outlet mouth 8 of the volute 7 centered with respect to the nozzle assembly 9. The nozzle assembly 9 is mounted on the support ring 10 of the tubine.
The problem, as is well known in the art, is that there is a differential of thermal expansion between the several component parts of the turbine assembly. This is because they are constructed of different materials and are differently positioned. For example, the volute 7 is made of thin sheet material. Consequently, it is heavily stressed by heat and this results in a high level of thermal expansion. The thermal expansion of the volute greatly exceeds that of the nozzle support ring 10. Moreover, due to the pressure differentials and the momentum of the gases between the inlet and the outlet of the turbine the annular mouth 8 is subjected to an upwardly lifting force. Once steady-state conditions are reached however, both the ring 10 andthe annular mouth 8 will have a known level of thermal expansion. This can be accurately determined by measuring the temperature at steady-state conditions. These differentials of thermal expansion must be compensated for in order to keep the aft end of the turbine assembly centered with respect to the nozzle assembly.
Therefore, in accordance with this invention the upper retaining half ring 12 is secured by bolts 11 to the I
... . .
,. j , - ~3311~V
external top section of the nozzle support ring 10 as shown in Fig. 1. This provides a gap 14 the width of which corresponds to the differential of thermal expansion between the nozzle support ring 10 and the annular mouth 8, When steady state conditions are reached the outer edge of the annular mouth 8 will abut the half ring 12 and therefore constantly be kept centered relative to the nozzle 9. In this way the problem of relative centering is solved at steady-state conditions.
The invention also centers the annular mouth during the initial period between starting the gas turbine and the attainment of normal working or steady state conditions.
During this initial period, the differential of thermal expansion between the annular mouth 8 and the nozzle support ring 10 is actually greater than that during the steady state condition. This is because the aft end of the volute 7 heats more rapidly than the ring 10. This differential results in a more rapid expansion of the annular mouth 8 than that of the ring 10. During this transitional phase, there is also more rapid expansion of the annular mouth 8 than that of the upper retaining half ring 12 with the concomitant stresses due to the interference between the annular mouth 8 and the upper retaining half ring 12. To solve this differential expansion problem during the initial period, the lower retaining half ring 13 is secured by bolts 11 to the lower portion of the ring 10 as shown in Fig. 1.
Lower retaining half ring 13 is radially norrower than the upper retaining half ring 12. As shown in Fig. 2, the 3~ outside diameter of the upper and the lower retaining half rings are the same, but the inside diameter of the lower retaining half ring 13 is greater than the inside diameter of the upper retaining half ring 12. Therefore, a radial expansion gap 15 is provided exceeding the radial expansion , .
,' i ,.~ .
~331~
.
gap 14. In this way, the aft end of the annular mouth 8 is able to expand without creating abnormal force upon the upper retaining half ring 12 during the opexating.
Thuq, a composite expansion compensating ring structure is provided which, by selection of different radial dimensions of annular sections, allows compensation of thermal expansion under both initial operating conditions and under :~:
normal or steady state conditions. - ~ :
,: :, -. i . .
... . .
use of keys enables effective centering to be maintained, -~:~
even in gas turbines of high compressin ratio.
According to the present invention there is provided a device for keeping an annular outlet mouth of a gas volute :~
always centered about a nozzle assembly in a gas turbine, :
characterised by comprising two retaining half-rings, a lower half-ring and an upper half-ring, which are fixed to a nozzel support ring to embrace said annular mouth, the lower half-ring having an inner radius greater than that of the upper half-ring, which forms with an outer flange of said annular outlet mouth of the volute a predetermined gap arranged to compensate a differential expansion between said annular mouth and said nozzle support ring.
According to the present invention there is also provided a device for centering an annular outlet mouth of a gas volute relative to a nozzle assembly in a gas turbine wherein the nozzle assembly has a nozzle support ring surrounding the annular outlet mouth, comprising~
a) a first retaining diametrically divided ring attached to the nozzle support ring, wherein said first retaining ~ ~
ring has an outer radius and an inner radius; and -:
b) a second retaining diametrically divided ring attached to the nozzle support ring, wherein said second retaining ring has an outer radius and an inner radius, wherein said ~ :
outer radius of said second retaining ring is equal to said~ :~
outer radius of said first retaining ring and said inner -radius of said second retaining ring is greater than said :~
inner radius of said first retaining ring thereby forming a gap wherein said gap is effective to compensate for~:
differential expansion between the annular outlet mouth and :
the nozzle support ring.
, ,~ . .
~ 3 3 :~`
The invention is described in detail hereinafter with reference to the accompanying drawings which illustrate a preferred embodiment thereof given by way of non-limiting example in that technical or constructional modifications can be made thereto but without leaving the scope of the present invention.
In said drawings:
:
Fig. 1 is partial lateral section through a gas turbine using the device of the invention;
, Fig. la is an enlarged detail drawing showing the gap 14 shown in Fig. l;
Fig. lb is an enlarged detail drawing showing the gap 15 shown in Fig. l;
Fig. 2 is a partial front section on the line A-A of Fig. 1.
~ ' In the figures, the reference numeral 1 indicates a gas turbine casing which on bearings 2 rotatably supports the shaft 3 carrying the discs 4 of the turbine blades 5. Line 3a is the centerline of the shaft 3. The combustion chamber 6 is connected to a gas volute 7 the annular outlet mouth 8 of which faces the zone comprising the nozzles 9, which are supported radially by a nozzle support ring 10 supported by the turbine casing 1.
In order to keep the annular outlet mouth 8 always centered about the nozzle assembly 9, two retaining diametrically divided half-rings 12 and 13 are fixed above and below of the centerline 3a of the shaft 3 on the nozzle support ring 10 by bolts 11 to embrace said annular mouth 8 in such a ., ~ ........................................ ..
.. - '.', .
~ ~ 3 ~
manner as to leave a predetermined gap 14 between the upper half-ring 12 and the outer flange 7' of said annular outlet mouth 8. In addition, ~he lower half-ring 13 has a larger inner radius than the upper half-ring 12 (see Fig. 2 specifically), so that a greater empty space 15 is available.
:
The present invention thus keeps the annular outlet mouth 8 of the volute 7 centered with respect to the nozzle assembly 9. The nozzle assembly 9 is mounted on the support ring 10 of the tubine.
The problem, as is well known in the art, is that there is a differential of thermal expansion between the several component parts of the turbine assembly. This is because they are constructed of different materials and are differently positioned. For example, the volute 7 is made of thin sheet material. Consequently, it is heavily stressed by heat and this results in a high level of thermal expansion. The thermal expansion of the volute greatly exceeds that of the nozzle support ring 10. Moreover, due to the pressure differentials and the momentum of the gases between the inlet and the outlet of the turbine the annular mouth 8 is subjected to an upwardly lifting force. Once steady-state conditions are reached however, both the ring 10 andthe annular mouth 8 will have a known level of thermal expansion. This can be accurately determined by measuring the temperature at steady-state conditions. These differentials of thermal expansion must be compensated for in order to keep the aft end of the turbine assembly centered with respect to the nozzle assembly.
Therefore, in accordance with this invention the upper retaining half ring 12 is secured by bolts 11 to the I
... . .
,. j , - ~3311~V
external top section of the nozzle support ring 10 as shown in Fig. 1. This provides a gap 14 the width of which corresponds to the differential of thermal expansion between the nozzle support ring 10 and the annular mouth 8, When steady state conditions are reached the outer edge of the annular mouth 8 will abut the half ring 12 and therefore constantly be kept centered relative to the nozzle 9. In this way the problem of relative centering is solved at steady-state conditions.
The invention also centers the annular mouth during the initial period between starting the gas turbine and the attainment of normal working or steady state conditions.
During this initial period, the differential of thermal expansion between the annular mouth 8 and the nozzle support ring 10 is actually greater than that during the steady state condition. This is because the aft end of the volute 7 heats more rapidly than the ring 10. This differential results in a more rapid expansion of the annular mouth 8 than that of the ring 10. During this transitional phase, there is also more rapid expansion of the annular mouth 8 than that of the upper retaining half ring 12 with the concomitant stresses due to the interference between the annular mouth 8 and the upper retaining half ring 12. To solve this differential expansion problem during the initial period, the lower retaining half ring 13 is secured by bolts 11 to the lower portion of the ring 10 as shown in Fig. 1.
Lower retaining half ring 13 is radially norrower than the upper retaining half ring 12. As shown in Fig. 2, the 3~ outside diameter of the upper and the lower retaining half rings are the same, but the inside diameter of the lower retaining half ring 13 is greater than the inside diameter of the upper retaining half ring 12. Therefore, a radial expansion gap 15 is provided exceeding the radial expansion , .
,' i ,.~ .
~331~
.
gap 14. In this way, the aft end of the annular mouth 8 is able to expand without creating abnormal force upon the upper retaining half ring 12 during the opexating.
Thuq, a composite expansion compensating ring structure is provided which, by selection of different radial dimensions of annular sections, allows compensation of thermal expansion under both initial operating conditions and under :~:
normal or steady state conditions. - ~ :
,: :, -. i . .
... . .
Claims (2)
1. A device for keeping an annular outlet mouth of a gas volute always centered about a nozzle assembly in a gas turbine, characterised by comprising two retaining half-rings, a lower half-ring and an upper half-ring, which are fixed to a nozzel support ring to embrace said annular mouth, the lower half-ring having an inner radius greater than that of the upper half-ring, which forms with an outer flange of said annular outlet mouth of the volute a predetermined gap arranged to compensate a differential expansion between said annular mouth and said nozzle support ring.
2. A device for centering an annular outlet mouth of a gas volute relative to a nozzle assembly in a gas turbine wherein the nozzle assembly has a nozzle support ring surrounding the annular outlet mouth, comprising:
a) a first retaining diametrically divided ring attached to the nozzle support ring, wherein said first retaining ring has an outer radius and an inner radius; and b) a second retaining diametrically divided ring attached to the nozzle support ring, wherein said second retaining ring has an outer radius and an inner radius, wherein said outer radius of said second retaining ring is equal to said outer radius of said first retaining ring and said inner radius of said second retaining ring is greater than said inner radius of said first retaining ring thereby forming a gap wherein said gap is effective to compensate for differential expansion between the annular outlet mouth and the nozzle support ring.
a) a first retaining diametrically divided ring attached to the nozzle support ring, wherein said first retaining ring has an outer radius and an inner radius; and b) a second retaining diametrically divided ring attached to the nozzle support ring, wherein said second retaining ring has an outer radius and an inner radius, wherein said outer radius of said second retaining ring is equal to said outer radius of said first retaining ring and said inner radius of said second retaining ring is greater than said inner radius of said first retaining ring thereby forming a gap wherein said gap is effective to compensate for differential expansion between the annular outlet mouth and the nozzle support ring.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| IT20275A/88 | 1988-04-21 | ||
| IT8820275A IT1216611B (en) | 1988-04-21 | 1988-04-21 | DEVICE FOR KEEPING THE ANNULAR OUTLET MOUTH OF THE GAS CONVEYOR ALWAYS CENTERED COMPARED TO THE NOZZLE GROUP OF AN AGAS TURBINE. |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1331100C true CA1331100C (en) | 1994-08-02 |
Family
ID=11165353
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000596600A Expired - Fee Related CA1331100C (en) | 1988-04-21 | 1989-04-13 | Device for keeping the annular outlet mouth of the gas volute always centered about the nozzle assembly in a gas turbine |
Country Status (7)
| Country | Link |
|---|---|
| JP (1) | JP2707134B2 (en) |
| CA (1) | CA1331100C (en) |
| CH (1) | CH675453A5 (en) |
| DE (1) | DE3913223A1 (en) |
| FR (1) | FR2630499B1 (en) |
| GB (1) | GB2218157B (en) |
| IT (1) | IT1216611B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1744014A1 (en) * | 2005-07-13 | 2007-01-17 | Siemens Aktiengesellschaft | Gas turbine inlet guide vane mounting arrangement |
| JP4584080B2 (en) * | 2005-08-31 | 2010-11-17 | 株式会社日立製作所 | Regenerative single can gas turbine |
| WO2007104587A2 (en) * | 2006-03-15 | 2007-09-20 | Siemens Aktiengesellschaft | Method for mounting a mixing housing in a gas turbine, and adjusting device therefor |
| RU2544020C1 (en) * | 2014-01-15 | 2015-03-10 | Открытое акционерное общество "Газэнергосервис" | Method of mounting inner inserts of turbine casing of gas compressor unit |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH354986A (en) * | 1956-10-02 | 1961-06-15 | Svenska Turbin Aktiebolaget Lj | Housing for a turbine driven by an elastic fluid |
| US3609968A (en) * | 1970-04-29 | 1971-10-05 | Westinghouse Electric Corp | Self-adjusting seal structure |
| GB2102897B (en) * | 1981-07-27 | 1985-06-19 | Gen Electric | Annular seals |
| DE3469205D1 (en) * | 1983-03-04 | 1988-03-10 | Bbc Brown Boveri & Cie | Connection between the hot and cold parts of an uncooled turbo charger |
-
1988
- 1988-04-21 IT IT8820275A patent/IT1216611B/en active
-
1989
- 1989-04-12 CH CH1386/89A patent/CH675453A5/it not_active IP Right Cessation
- 1989-04-13 CA CA000596600A patent/CA1331100C/en not_active Expired - Fee Related
- 1989-04-19 GB GB8908879A patent/GB2218157B/en not_active Expired - Lifetime
- 1989-04-19 JP JP1097679A patent/JP2707134B2/en not_active Expired - Fee Related
- 1989-04-21 FR FR898905309A patent/FR2630499B1/en not_active Expired - Fee Related
- 1989-04-21 DE DE3913223A patent/DE3913223A1/en active Granted
Also Published As
| Publication number | Publication date |
|---|---|
| GB2218157B (en) | 1992-06-10 |
| IT1216611B (en) | 1990-03-08 |
| CH675453A5 (en) | 1990-09-28 |
| JP2707134B2 (en) | 1998-01-28 |
| JPH01305133A (en) | 1989-12-08 |
| FR2630499A1 (en) | 1989-10-27 |
| DE3913223A1 (en) | 1989-11-02 |
| IT8820275A0 (en) | 1988-04-21 |
| FR2630499B1 (en) | 1991-11-22 |
| GB2218157A (en) | 1989-11-08 |
| GB8908879D0 (en) | 1989-06-07 |
| DE3913223C2 (en) | 1991-07-11 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MKLA | Lapsed |