EP0103260A2 - Clearance control for turbine blade tips - Google Patents
Clearance control for turbine blade tips Download PDFInfo
- Publication number
- EP0103260A2 EP0103260A2 EP83108779A EP83108779A EP0103260A2 EP 0103260 A2 EP0103260 A2 EP 0103260A2 EP 83108779 A EP83108779 A EP 83108779A EP 83108779 A EP83108779 A EP 83108779A EP 0103260 A2 EP0103260 A2 EP 0103260A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- turbine
- guide vane
- shrouds
- vane segments
- casing
- 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.)
- Withdrawn
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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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
- F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
-
- 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
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
Definitions
- This invention relates to a turbine in which clearance between turbine blade tips and shrouds is controlled.
- the clearance between turbine blade tips and shrouds causes fluid used to drive the turbine to leak. If the clearance is large, the amount of the leakage increases, resulting in deteriorated heat efficiency of turbines such as a gas turbine or a steam 'turbine.
- An object of the invention is to provide a turbine whose clearance between turbine blade tips and shrouds can be controlled automatically during operation by simple structure.
- shrouds are mounted to a body stationary in the rotating direction of a turbine rotor and movable freely in a radial direction under expansion thereof, and which can be expanded radially from the centre of said turbine rotor substantially in the same manner as said turbine blades.
- FIG 1 there is illustrated a part of a gas turbine in which a turbine rotor assembly 10 is disposed downstream of a guide vane assembly 11 inside a turbine casing 12.
- the turbine rotor assembly 10 is rotated by high temperature gas which flows from an entrance site A of the turbine, i.e. an exit of combustion chamber to an exit site B of the turbine rotor assembly 10.
- the turbine rotor assembly 10 comprises an annular disc 13 fixed to a turbine rotor 14 which is supported rotatably by a bearing 15 and a plurality of turbine blades 16 attached by dave-tail structure around the annular disc 13.
- the turbine blades 16 exposed to the high temperature gas expand radially from the centre of the turbine rotor 14 corresponding to a standard position of expansion.
- the guide vane assembly 11 comprises a plurality of guide vane segments 17, each of which forming a body, which are mounted to a stationary part 18 of a bearing 15 through pins 19 respectively and an annular member 20.
- the guide vane segments 17 are disposed around the annular member 20 as shown Figure 2.
- the guide vane segments 17 are diposed radially free against the casing 12.
- the guide vane segments 17 expand radially from the center line of the stationary part of the bearing 18, i.e. the centre of the bearing 15 or the centre line (c-c) of the turbine rotor 14, in the same manner as the turbine blades 16.
- the guide vane segments 17 each is a united body providing guide vanes 21, an outer endwall 22, a pair of projections 23a, 23b, an inner endwall 24 and a pair of flanges 25a, 25b.
- the inner endwall 24 extended substantially in parallel with the shaft of the turbine at the inner side of the guide vanes 21.
- the flanges 25a, 25b provide pin holes for pin 19 to be inserted.
- the outer endwall 22 extends substantially in parallel with the shaft of the turbine at the outer side of the guide vanes 21 and also extends downstream so as to face the turbine blade tip 26. Thus extended portion of the outer endwall 22 corresponds to a shroud 27.
- the shroud 27 may be constructed separately and be fixed to the outer endwall 22.
- a pair of projections 23a, 23b extending outward from the guide vanes 21 are disposed respectively so as to face a pair of support rings 28, 29 which extend inward from the casing 12.
- the projections 23a, 23b provide a plurality of coaxial slots 30a, 30b so that cooling fluid which may be flown in a space 31 to cool the guide vane segments 17 can be sealed by labyrinth effect based on the slots 30a, 30b.
- a seal plate 34 to seal in a radial direction is inserted as shown in figure 3.
- the same seal mechanism comprising the slot 32 and the seal plate 34 as mentioned above is adapted at circumferential end portions of the inner endwall 24 (not shown).
- parallel meandering slots are formed at both ends 33a, 33b of the outer endwall 22 so that each slot of adjacent endwalls 22 can be engaged with each other, resulting in sealing contact surface of each outer endwall 22.
- the guide vane segments 17 are movable radially against the casing 12, sealing the space 31. Accordingly, as already mentioned above, the guide vane segments 17 can expand radially during operation from the centre of the shaft in the same manner as the turbine blades 16 without being undue affected by p.e. thermal expansion of the casing 12.
- Each amount of thermal expansion of the guide vane segments 17 and turbine blades 16 is almost the same because temperature of the gas is nearly the same both at the guide vane segments 17 and at-the turbine blades 16. Therefore the clearance between the turbine blade tips 26 and the shrouds 27 mounted to the guide vane segments 17 is kept constant, as shown in Figure 4, in all the operation modes, i.e. during accelaration, steady state running and deceleration.
- clearance can be set very small without necessity to take into account conflict between the turbine blade tips 26 and the shrouds 27 due to transient change of the clearance during operation.
- the pressure of the cooling fluid in the space 31 is adjusted to the same static pressure as that of the gas passing the guide vanes 21 and the turbine blades 16 so that deformation of the shrouds 27 can be avoided by cancelling each force acting on each side of the shrouds 27.
- Such eliminatinq of deformation of the shrouds 27 can be further improved by the embodiment illustrated in Figure 5. That is, in practise two pressures of the gas are different at positions of the guide vane 21 and the turbine blade 16 respectively.
- the space for the cooling fluid is divided into two compartments, i.e.
- an upstream compartment 50 and a downstream compartment 51 by a dividing plate 52 of which one end is fixed to a portion 53 of the outer endwall 22, and the other end is inserted in a slot 54 of the casing 12.
- this plate 52 slides in the slot 54, maintaining sealing between the other end portion of the dividing plate 52 and the casing 12.
- Said end portion 53 is chosen at a region corresponding to a guide vane end portion adjacent to the turbine blade 16.
- the cooling fluid supplied from an opening 55 flows from the upstream compartment 50 to the downstream compartment 51 through an orifice 56 in the dividing plate 52.
- the pressure in the upstream compartment 50 can be the same pressure as the gas pressure at the guide vane 21.
- the size of the orifice 56 is chosen so that the pressure reduced thereby is the same pressure as that of the gas passing at the turbine blade 16.
- the cooling fluid can flow out through small gap between projections 23a, 23b and support rings 28, 29. This embodiment can serve to allow the clearance to be set even smaller without the negative influence on the shrouds 27.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- This invention relates to a turbine in which clearance between turbine blade tips and shrouds is controlled.
- The clearance between turbine blade tips and shrouds causes fluid used to drive the turbine to leak. If the clearance is large, the amount of the leakage increases, resulting in deteriorated heat efficiency of turbines such as a gas turbine or a steam 'turbine.
- In a conventional turbine whose shrouds are mounted to a turbine casing, it is known that the clearance changes transiently during operation of the turbine due to relative thermal expansion among members constructing the turbine. There have been proposals to control such a transient change of the clearance. However, methods controlling such relative thermal expansion by blowing cold air onto the casing and shrouds or heating the above-mentioned structure of the turbine require lots of devices such as gap detectors, valves and their control apparatuses. A method mounting shrouds to the casing through guide vane assemblies pivotally mounted thereto, which is shown in UK patent application GB 2 061 396A, causes its mechanism to be complex and also causes design of the mechanism to be difficult.
- An object of the invention is to provide a turbine whose clearance between turbine blade tips and shrouds can be controlled automatically during operation by simple structure.
- According to one aspect of the invention shrouds are mounted to a body stationary in the rotating direction of a turbine rotor and movable freely in a radial direction under expansion thereof, and which can be expanded radially from the centre of said turbine rotor substantially in the same manner as said turbine blades. This invention makes it possible to keep the clearance at a small value in all the operation modes without providing a complex clearance control device.
- Other advantages and optional features of the invention will be described in more detail with reference to preferred embodiments illustrated in the accompanying drawings, in which:
- Figure 1 is a schematic view of a turbine in accordance with the present invention;
- Figure 2 is a plan view taken along line II-II of Figure 1;
- Figure 3 is a sectional view taken along line III-III of Figure 2;
- Figure 4 shows a relationship between the clearance and time of operation; and
- Figure 5 is a schematic view, corresponding to Figure 1, of another embodiment.
- In Figure 1, there is illustrated a part of a gas turbine in which a
turbine rotor assembly 10 is disposed downstream of aguide vane assembly 11 inside aturbine casing 12. Theturbine rotor assembly 10 is rotated by high temperature gas which flows from an entrance site A of the turbine, i.e. an exit of combustion chamber to an exit site B of theturbine rotor assembly 10. - The
turbine rotor assembly 10 comprises anannular disc 13 fixed to aturbine rotor 14 which is supported rotatably by abearing 15 and a plurality ofturbine blades 16 attached by dave-tail structure around theannular disc 13. Theturbine blades 16 exposed to the high temperature gas expand radially from the centre of theturbine rotor 14 corresponding to a standard position of expansion. - The
guide vane assembly 11 comprises a plurality ofguide vane segments 17, each of which forming a body, which are mounted to astationary part 18 of a bearing 15 throughpins 19 respectively and anannular member 20. Theguide vane segments 17 are disposed around theannular member 20 as shown Figure 2. On the other hand, as described below, theguide vane segments 17 are diposed radially free against thecasing 12. Theguide vane segments 17 expand radially from the center line of the stationary part of thebearing 18, i.e. the centre of thebearing 15 or the centre line (c-c) of theturbine rotor 14, in the same manner as theturbine blades 16. - The
guide vane segments 17 each is a united body providingguide vanes 21, anouter endwall 22, a pair ofprojections inner endwall 24 and a pair offlanges inner endwall 24 extended substantially in parallel with the shaft of the turbine at the inner side of theguide vanes 21. Theflanges pin 19 to be inserted. Theouter endwall 22 extends substantially in parallel with the shaft of the turbine at the outer side of theguide vanes 21 and also extends downstream so as to face theturbine blade tip 26. Thus extended portion of theouter endwall 22 corresponds to ashroud 27. Theshroud 27 may be constructed separately and be fixed to theouter endwall 22. A pair ofprojections guide vanes 21 are disposed respectively so as to face a pair ofsupport rings casing 12. Theprojections coaxial slots space 31 to cool theguide vane segments 17 can be sealed by labyrinth effect based on theslots slots 32 atcircumferential end portions outer endwall 22. In each slot adjacent to each other aseal plate 34 to seal in a radial direction is inserted as shown in figure 3. The same seal mechanism comprising theslot 32 and theseal plate 34 as mentioned above is adapted at circumferential end portions of the inner endwall 24 (not shown). - As shown in Figure 2, parallel meandering slots are formed at both
ends outer endwall 22 so that each slot ofadjacent endwalls 22 can be engaged with each other, resulting in sealing contact surface of eachouter endwall 22. - Thus the
guide vane segments 17 are movable radially against thecasing 12, sealing thespace 31. Accordingly, as already mentioned above, theguide vane segments 17 can expand radially during operation from the centre of the shaft in the same manner as theturbine blades 16 without being undue affected by p.e. thermal expansion of thecasing 12. Each amount of thermal expansion of theguide vane segments 17 andturbine blades 16 is almost the same because temperature of the gas is nearly the same both at theguide vane segments 17 and at-theturbine blades 16. Therefore the clearance between theturbine blade tips 26 and theshrouds 27 mounted to theguide vane segments 17 is kept constant, as shown in Figure 4, in all the operation modes, i.e. during accelaration, steady state running and deceleration. Thus such clearance can be set very small without necessity to take into account conflict between theturbine blade tips 26 and theshrouds 27 due to transient change of the clearance during operation. Preferably, it is desired to select materials of the guide vane segments and the turbine blades whose coefficient of linear expansion each is close. In this case the clearance can be set much smaller. - In order to compare the above embodiment with a conventional one a characteristic of a conventional turbine of which guide vane segments are mounted to a casing is shown by a dotted line in Figure 4. That is, during acceleration increase of the temperature of the casing heat mass of which is extremely large tends to be delayed more than those of the guide vane segments and the turbine blades. As a result the turbine blades expands radially more rapidly than the guide vane segments whose thermal expansion is restricted by the casing. Therefore the clearance decreases first until the expansion of the turbine blades reaches steady-state (range C-D). Thereafter the clearance increases until the expansion of the guide vane segments reaches steady-state (range D-E). According to a conventional turbine, the clearance must be set relatively large so that the conflict between the turbine blades and the shrouds can be avoided at point D.
- Furthermore minimum clearance at point D for the conventional turbine is required to be much bigger than that for the invention as shown in figure 4. This is because clearance distribution in the circumferential direction of the conventional turbine cannot be uniform due to differences in stiffness of the casing and conditions of heat conduction of surrounding parts. In other words it is possible with this invention to set the clearance much smaller since support members of the guide vane segments such as the annular member have the above-mentioned uniformity.
- In the above embodiment the pressure of the cooling fluid in the
space 31 is adjusted to the same static pressure as that of the gas passing theguide vanes 21 and theturbine blades 16 so that deformation of theshrouds 27 can be avoided by cancelling each force acting on each side of theshrouds 27. Such eliminatinq of deformation of theshrouds 27 can be further improved by the embodiment illustrated in Figure 5. That is, in practise two pressures of the gas are different at positions of theguide vane 21 and theturbine blade 16 respectively. In order to cancel different pressure acting on theouter endwall 22, and particularly on theshroud 27, more precisely the space for the cooling fluid is divided into two compartments, i.e. anupstream compartment 50 and adownstream compartment 51, by a dividingplate 52 of which one end is fixed to aportion 53 of theouter endwall 22, and the other end is inserted in aslot 54 of thecasing 12. In case of thermal expansion of the dividingplate 52, thisplate 52 slides in theslot 54, maintaining sealing between the other end portion of the dividingplate 52 and thecasing 12. Saidend portion 53 is chosen at a region corresponding to a guide vane end portion adjacent to theturbine blade 16. The cooling fluid supplied from an opening 55 flows from theupstream compartment 50 to thedownstream compartment 51 through anorifice 56 in the dividingplate 52. The pressure in theupstream compartment 50 can be the same pressure as the gas pressure at theguide vane 21. The size of theorifice 56 is chosen so that the pressure reduced thereby is the same pressure as that of the gas passing at theturbine blade 16. The cooling fluid can flow out through small gap betweenprojections support rings shrouds 27.
Claims (10)
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP153923/82 | 1982-09-06 | ||
JP15392382A JPS5943905A (en) | 1982-09-06 | 1982-09-06 | Adjuster for gap at tip of rotor blade of axial flow turbine |
JP198986/82 | 1982-11-15 | ||
JP19898682A JPS5990706A (en) | 1982-11-15 | 1982-11-15 | Device for adjusting clearance at extremity end of moving blade of axial flow trubine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0103260A2 true EP0103260A2 (en) | 1984-03-21 |
EP0103260A3 EP0103260A3 (en) | 1984-09-26 |
Family
ID=26482405
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP83108779A Withdrawn EP0103260A3 (en) | 1982-09-06 | 1983-09-06 | Clearance control for turbine blade tips |
Country Status (1)
Country | Link |
---|---|
EP (1) | EP0103260A3 (en) |
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2206651A (en) * | 1987-07-01 | 1989-01-11 | Rolls Royce Plc | Turbine blade shroud structure |
US5868553A (en) * | 1996-05-08 | 1999-02-09 | Asea Brown Boveri Ag | Exhaust gas turbine of an exhaust gas turbocharger |
GB2380527A (en) * | 2001-08-11 | 2003-04-09 | Rolls Royce Plc | Gas turbine engine guide vane assembly with noise reduction |
CN100400797C (en) * | 2001-04-12 | 2008-07-09 | 西门子公司 | Combustion turbine with axial relative movel guide unit |
JP2008255989A (en) * | 2007-04-05 | 2008-10-23 | Alstom Technology Ltd | Clearance seal in blade of turbo machine |
WO2011035947A1 (en) | 2009-09-25 | 2011-03-31 | Evonik Rohmax Additives Gmbh | A composition to improve cold flow properties of fuel oils |
WO2012130535A1 (en) | 2011-03-25 | 2012-10-04 | Evonik Rohmax Additives Gmbh | A composition to improve oxidation stability of fuel oils |
US8347633B2 (en) | 2007-07-27 | 2013-01-08 | United Technologies Corporation | Gas turbine engine with variable geometry fan exit guide vane system |
US8418458B2 (en) | 2009-01-20 | 2013-04-16 | Williams International Co., L.L.C. | Turbocharger core |
US8459035B2 (en) | 2007-07-27 | 2013-06-11 | United Technologies Corporation | Gas turbine engine with low fan pressure ratio |
CN114607474A (en) * | 2022-03-21 | 2022-06-10 | 中国联合重型燃气轮机技术有限公司 | Stator blade clearance control system and gas turbine with same |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2849209A (en) * | 1950-10-11 | 1958-08-26 | Gen Electric | Nozzle construction for turbines |
US3532437A (en) * | 1967-11-03 | 1970-10-06 | Sulzer Ag | Stator blade assembly for axial-flow turbines |
GB1534660A (en) * | 1976-05-05 | 1978-12-06 | Stal Laval Turbin Ab | Sealing arrangement in a gas turbine |
GB2034415A (en) * | 1978-11-13 | 1980-06-04 | Gen Motors Corp | Turbine stator mounting |
GB2061396A (en) * | 1979-10-24 | 1981-05-13 | Rolls Royce | Turbine blade tip clearance control |
-
1983
- 1983-09-06 EP EP83108779A patent/EP0103260A3/en not_active Withdrawn
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2849209A (en) * | 1950-10-11 | 1958-08-26 | Gen Electric | Nozzle construction for turbines |
US3532437A (en) * | 1967-11-03 | 1970-10-06 | Sulzer Ag | Stator blade assembly for axial-flow turbines |
GB1534660A (en) * | 1976-05-05 | 1978-12-06 | Stal Laval Turbin Ab | Sealing arrangement in a gas turbine |
GB2034415A (en) * | 1978-11-13 | 1980-06-04 | Gen Motors Corp | Turbine stator mounting |
GB2061396A (en) * | 1979-10-24 | 1981-05-13 | Rolls Royce | Turbine blade tip clearance control |
Cited By (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2206651B (en) * | 1987-07-01 | 1991-05-08 | Rolls Royce Plc | Turbine blade shroud structure |
GB2206651A (en) * | 1987-07-01 | 1989-01-11 | Rolls Royce Plc | Turbine blade shroud structure |
US5868553A (en) * | 1996-05-08 | 1999-02-09 | Asea Brown Boveri Ag | Exhaust gas turbine of an exhaust gas turbocharger |
CN100400797C (en) * | 2001-04-12 | 2008-07-09 | 西门子公司 | Combustion turbine with axial relative movel guide unit |
GB2380527A (en) * | 2001-08-11 | 2003-04-09 | Rolls Royce Plc | Gas turbine engine guide vane assembly with noise reduction |
US6764276B2 (en) | 2001-08-11 | 2004-07-20 | Rolls-Royce Plc | Guide vane assembly |
GB2380527B (en) * | 2001-08-11 | 2004-10-27 | Rolls Royce Plc | A guide vane assembly |
JP2008255989A (en) * | 2007-04-05 | 2008-10-23 | Alstom Technology Ltd | Clearance seal in blade of turbo machine |
US8347633B2 (en) | 2007-07-27 | 2013-01-08 | United Technologies Corporation | Gas turbine engine with variable geometry fan exit guide vane system |
US8459035B2 (en) | 2007-07-27 | 2013-06-11 | United Technologies Corporation | Gas turbine engine with low fan pressure ratio |
US8418458B2 (en) | 2009-01-20 | 2013-04-16 | Williams International Co., L.L.C. | Turbocharger core |
EP2305753A1 (en) | 2009-09-25 | 2011-04-06 | Evonik RohMax Additives GmbH | A composition to improve cold flow properties of fuel oils |
WO2011035947A1 (en) | 2009-09-25 | 2011-03-31 | Evonik Rohmax Additives Gmbh | A composition to improve cold flow properties of fuel oils |
US10131776B2 (en) | 2009-09-25 | 2018-11-20 | Evonik Oil Additives Gmbh | Composition to improve cold flow properties of fuel oils |
WO2012130535A1 (en) | 2011-03-25 | 2012-10-04 | Evonik Rohmax Additives Gmbh | A composition to improve oxidation stability of fuel oils |
CN114607474A (en) * | 2022-03-21 | 2022-06-10 | 中国联合重型燃气轮机技术有限公司 | Stator blade clearance control system and gas turbine with same |
Also Published As
Publication number | Publication date |
---|---|
EP0103260A3 (en) | 1984-09-26 |
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PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
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AK | Designated contracting states |
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18W | Application withdrawn |
Withdrawal date: 19851203 |
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RIN1 | Information on inventor provided before grant (corrected) |
Inventor name: NODA, MASAMI Inventor name: KATO, YASUHIRO, MR. Inventor name: IKEGUCHI, TAKASHI Inventor name: KAWAIKE, KAZUHIKO Inventor name: WADA, KATSUO |