CA1221915A - Multi-chamber airfoil cooling insert for turbine vane - Google Patents
Multi-chamber airfoil cooling insert for turbine vaneInfo
- Publication number
- CA1221915A CA1221915A CA000495185A CA495185A CA1221915A CA 1221915 A CA1221915 A CA 1221915A CA 000495185 A CA000495185 A CA 000495185A CA 495185 A CA495185 A CA 495185A CA 1221915 A CA1221915 A CA 1221915A
- Authority
- CA
- Canada
- Prior art keywords
- chambers
- rearward
- insert
- ports
- impingement
- 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
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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
- F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
- F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
Abstract
ABSTRACT OF THE DISCLOSURE
An airfoil-shaped turbine vane has a single, unitary insert 22 therein which is divided by a plurality of radially extending ribs 38, 40, and 42 into a forward chamber 30, and successively rearward chambers 32, 34, and 36, with throttling means 48 being provided at the inlet to the rearward chambers while the airflow 46 to the forward chamber is not restricted, so that the forward chamber is at a higher pressure than the rearward chambers so that the impingement jets through the impingement ports 56 are at a higher velocity than the impingement jets through the impingement ports 58 and 60 from the lower pressure rear-ward chambers.
An airfoil-shaped turbine vane has a single, unitary insert 22 therein which is divided by a plurality of radially extending ribs 38, 40, and 42 into a forward chamber 30, and successively rearward chambers 32, 34, and 36, with throttling means 48 being provided at the inlet to the rearward chambers while the airflow 46 to the forward chamber is not restricted, so that the forward chamber is at a higher pressure than the rearward chambers so that the impingement jets through the impingement ports 56 are at a higher velocity than the impingement jets through the impingement ports 58 and 60 from the lower pressure rear-ward chambers.
Description
MULTI-CHAMB~R AI~FOIL COOLING INSERT
FOR TURBINE ~ANE
BACKGROUND 0~ THE INVENTION
Field of the Inventi.on:
This invention pertains to the art of turbine airfoil vanes provided with an insert, with the arrangement as a whole providing for air cooling of the vanes.
In the turbine art, it is known that different stages of the stator vanes require different levels of cooling. The vane structure with which this invention is concerned is of a character and in a stage calling for what those knowledgeable in the art would consider to be a low or a moderate level of cooling, which level of cooling can be carried out by the use of impingement jets directed against the interior walls of the vane. As is also known, even with those vanes which do not require a high level of cooling, the degree of cooling required at different locations on the vane may differ, with the leading edge region of the vane typically having a relatively higher heat load while downstream and toward the trailing edge of the vane the heat load may be significantly lower.
It is an aim of this invention to provide a vane and insert structure in which a vane having a single internal cavity is provided with a single, unitary, hollow insert provided with a chamber arrangement and jet impinge-ment ports all tailored to relate the impingement cooling of the walls to the extexnal heat load.
FOR TURBINE ~ANE
BACKGROUND 0~ THE INVENTION
Field of the Inventi.on:
This invention pertains to the art of turbine airfoil vanes provided with an insert, with the arrangement as a whole providing for air cooling of the vanes.
In the turbine art, it is known that different stages of the stator vanes require different levels of cooling. The vane structure with which this invention is concerned is of a character and in a stage calling for what those knowledgeable in the art would consider to be a low or a moderate level of cooling, which level of cooling can be carried out by the use of impingement jets directed against the interior walls of the vane. As is also known, even with those vanes which do not require a high level of cooling, the degree of cooling required at different locations on the vane may differ, with the leading edge region of the vane typically having a relatively higher heat load while downstream and toward the trailing edge of the vane the heat load may be significantly lower.
It is an aim of this invention to provide a vane and insert structure in which a vane having a single internal cavity is provided with a single, unitary, hollow insert provided with a chamber arrangement and jet impinge-ment ports all tailored to relate the impingement cooling of the walls to the extexnal heat load.
2 ~ LS
SUMMARY OF THE INVENTION
__ __ __ In accordance with the invention, the insert is provided with a plurality of radially extending partition means to divide the interior thereof into a single forward chamber in the leading edge portion of the vane, and at least two separate, successively rearward chambers in at least partial communication with each other, a plurality of impingement ports in the walls of all of said chambers, one radial end portion of all the chambers being in communica-tion with a source of cooling air, and with means forthrottling the flow into the rearward chambers so that the orward chamber is a relatively higher pressure than said rearward chambers and so the impingement jets through the ports of said forward chamber against said interior vane walls of said leading edge portion are at a significantly higher velocity than the impingement jets exiting the ports of the rearward chambers~.
BRIEF DESCRIPTION OF THE DRA~lINGS
Figure 1 is a typical chordwise sectional view through the vane and insert as would appear from a section taken along the line I-I of Figure 2; and Figure 2 is a view partly in elevation and partly in section of the vane and insert, and yenerally corre-sponding to a view taken along the line II-II of Figure l.
DESCRIPTION OF THE PREFERRED EMBODIMENT
Referring to Figure 1, the hollow vane having a single internal cavity is defined by the leading edge section generally designated 12, a concave sidewall 14, a convex sidewall 16, the downstream portlons of these opposite sidewalls defining a trailing edge portion gener-ally designated 18 and provided with a slot 2~ therein.
The general direction of the hot gas past the vane is as indicated by the dash line arrow in Figure 1.
The single, unitary, air-cooling, hollow insert generally designated 22 has an airfoil shape in cross section which is generally complementary to the vane airfoil shape, and extends in a chordwise direction for 3L2~ S
substantially the entire extent of the vane cavity. While the insert does have -the overall shape of an airoil, it may be seen in Figure 1 that at the leading edge portion 24 the insert is bulyed somewhat, a similar bulged arrangement being provided at the trailing edge portion 26. The intermediate portion 28 has walls which are basically uniformly spaced from the vane walls throughout the inter-mediate extent between the front and rear bulges.
The unitary insert 22 has its interior divided into a forward chamber 30 and successively rearward cham-bers 32, 34, and 36, by the radially extending partition means 38, 40, and 42, which also perorm a structural tying function.
The radially inner ends of all of the chambers are closed while the radially outer ends of the chambers are in communication with a source of cooling air. As may be best understood from Figure 2, the radially outer end 44 is completely open so that cooling air flows directly into the forward chamber 30 as indicated by the arrow 46 in Figure 2. While the rearward chambers 32, 34, and 36 are also in communication with the source of cooling air, the flow into these chambers is throttled by means of a radial extension 48 of the insert comprising opposite walls 50 capped by plate 52 which prevents the direct admission of the cooling air into the rearward chambers in the fashion in which the forward chambers receives its air, the cooling air being throttled into the rearward chambers by the provision of the holes 54 in the walls 50. The throttling results in the rearward chambers being at a lower pressure than the forward chamber 30.
Referring to both figures, all of the chambers are provided with impingement ports in their sidewalls.
Those ports provided in the forward chamber sidewalls are identified by the numeral 56 as best seen in Figure 1. The impingement ports in the convex sidewall o the insert or the rearward chambers are designated 58 while those in the concave wall are designated 60. As is best seen in Figure
SUMMARY OF THE INVENTION
__ __ __ In accordance with the invention, the insert is provided with a plurality of radially extending partition means to divide the interior thereof into a single forward chamber in the leading edge portion of the vane, and at least two separate, successively rearward chambers in at least partial communication with each other, a plurality of impingement ports in the walls of all of said chambers, one radial end portion of all the chambers being in communica-tion with a source of cooling air, and with means forthrottling the flow into the rearward chambers so that the orward chamber is a relatively higher pressure than said rearward chambers and so the impingement jets through the ports of said forward chamber against said interior vane walls of said leading edge portion are at a significantly higher velocity than the impingement jets exiting the ports of the rearward chambers~.
BRIEF DESCRIPTION OF THE DRA~lINGS
Figure 1 is a typical chordwise sectional view through the vane and insert as would appear from a section taken along the line I-I of Figure 2; and Figure 2 is a view partly in elevation and partly in section of the vane and insert, and yenerally corre-sponding to a view taken along the line II-II of Figure l.
DESCRIPTION OF THE PREFERRED EMBODIMENT
Referring to Figure 1, the hollow vane having a single internal cavity is defined by the leading edge section generally designated 12, a concave sidewall 14, a convex sidewall 16, the downstream portlons of these opposite sidewalls defining a trailing edge portion gener-ally designated 18 and provided with a slot 2~ therein.
The general direction of the hot gas past the vane is as indicated by the dash line arrow in Figure 1.
The single, unitary, air-cooling, hollow insert generally designated 22 has an airfoil shape in cross section which is generally complementary to the vane airfoil shape, and extends in a chordwise direction for 3L2~ S
substantially the entire extent of the vane cavity. While the insert does have -the overall shape of an airoil, it may be seen in Figure 1 that at the leading edge portion 24 the insert is bulyed somewhat, a similar bulged arrangement being provided at the trailing edge portion 26. The intermediate portion 28 has walls which are basically uniformly spaced from the vane walls throughout the inter-mediate extent between the front and rear bulges.
The unitary insert 22 has its interior divided into a forward chamber 30 and successively rearward cham-bers 32, 34, and 36, by the radially extending partition means 38, 40, and 42, which also perorm a structural tying function.
The radially inner ends of all of the chambers are closed while the radially outer ends of the chambers are in communication with a source of cooling air. As may be best understood from Figure 2, the radially outer end 44 is completely open so that cooling air flows directly into the forward chamber 30 as indicated by the arrow 46 in Figure 2. While the rearward chambers 32, 34, and 36 are also in communication with the source of cooling air, the flow into these chambers is throttled by means of a radial extension 48 of the insert comprising opposite walls 50 capped by plate 52 which prevents the direct admission of the cooling air into the rearward chambers in the fashion in which the forward chambers receives its air, the cooling air being throttled into the rearward chambers by the provision of the holes 54 in the walls 50. The throttling results in the rearward chambers being at a lower pressure than the forward chamber 30.
Referring to both figures, all of the chambers are provided with impingement ports in their sidewalls.
Those ports provided in the forward chamber sidewalls are identified by the numeral 56 as best seen in Figure 1. The impingement ports in the convex sidewall o the insert or the rearward chambers are designated 58 while those in the concave wall are designated 60. As is best seen in Figure
3~
2, all of the impingement ports are in ro~"s ~Jhich eY.tend generally radially As may be seen from ~igure 1, the rows of ports 56 of the forward chamber are more widely spaced from each other than the rows of ports from the rearward chambers on the convex side, and most of the concave side with the exception of the spacing of the rows of ports of the concave side of the first low-pressure chamber 32. It is also noted that the three rearward chambers are open to each other through the provision of a series of ports 62 in both of the partitions or ribs 40 and 42. The rearward chambers are also in open communication ~ith each other at the radially outer portion of the chambers by virtue of the partitions 40 and 42 stopping short of the space 64 at the radially outer ends of the chambers.
The insert has dimples 66 embossed outwardly in its leading edge portion and similar dimples 68 in its trailing edge portion to properly space the insert walls from the vane walls.
With the arrangement as shown and described, the forward chamber 30 is maintained at a higher pressure than the rearward chambers 32, 34, and 36, so that the cooling jets issuing from the forward chamber are projected at a higher velocity than those exiting through the ports of the rearward chambers so that the higher velocity jets are projected at the higher heat load leading edge and forward convex surface areas of the vane, while the jets issuing from the lower pressure rearward chambers are projected at a lower velocity for cooling the relatively lower heat load regions of the airfoil vane. The relatively closer spaced rows of ports throughout the midchord region is to obtain more uniform cooling than would be obtained with widely-spaced high velocity jets.
Typical pressures at which the chambers can be maintained may be in order of, for example, 160 psig (1102 E+03PA) for the forward chamber, 155 psig (1068 E+03Pa) for the rearward chambers, with the pressures in the spaces q~
between the insert and the opposincJ vane walls bein~ 150 psig ( 1033 E~03Pa) .
2, all of the impingement ports are in ro~"s ~Jhich eY.tend generally radially As may be seen from ~igure 1, the rows of ports 56 of the forward chamber are more widely spaced from each other than the rows of ports from the rearward chambers on the convex side, and most of the concave side with the exception of the spacing of the rows of ports of the concave side of the first low-pressure chamber 32. It is also noted that the three rearward chambers are open to each other through the provision of a series of ports 62 in both of the partitions or ribs 40 and 42. The rearward chambers are also in open communication ~ith each other at the radially outer portion of the chambers by virtue of the partitions 40 and 42 stopping short of the space 64 at the radially outer ends of the chambers.
The insert has dimples 66 embossed outwardly in its leading edge portion and similar dimples 68 in its trailing edge portion to properly space the insert walls from the vane walls.
With the arrangement as shown and described, the forward chamber 30 is maintained at a higher pressure than the rearward chambers 32, 34, and 36, so that the cooling jets issuing from the forward chamber are projected at a higher velocity than those exiting through the ports of the rearward chambers so that the higher velocity jets are projected at the higher heat load leading edge and forward convex surface areas of the vane, while the jets issuing from the lower pressure rearward chambers are projected at a lower velocity for cooling the relatively lower heat load regions of the airfoil vane. The relatively closer spaced rows of ports throughout the midchord region is to obtain more uniform cooling than would be obtained with widely-spaced high velocity jets.
Typical pressures at which the chambers can be maintained may be in order of, for example, 160 psig (1102 E+03PA) for the forward chamber, 155 psig (1068 E+03Pa) for the rearward chambers, with the pressures in the spaces q~
between the insert and the opposincJ vane walls bein~ 150 psig ( 1033 E~03Pa) .
Claims (6)
1. The combination comprising;
an airfoil-shaped, hollow, turbine vane having a leading edge wall, and a trailing edge portion with an exit air slot therein, and pressure and suction sidewalls defining a single internal cavity in communication with said exit air slot;
a single, unitary, air-cooling, hollow insert, of generally complementary airfoil shape in cross section, located in said cavity and extending in a chordwise direc-tion for substantially the entire extent of said cavity;
a plurality of radially extending partition means in said insert dividing the interior thereof into a forward chamber in the leading edge portion of said vane, and at least two separate, successively rearward chambers in communication with each other;
a plurality of impingement ports in the insert walls of all of said chambers;
one radial end portion of said chambers being in communication with a source of cooling air;
means for throttling the flow into said rearward chambers so that said forward chamber is at a relatively higher pressure than said rearward chambers and so the impingement jets through said ports of said forward chamber against said interior vane walls of said leading edge portion are at the significantly higher velocity than the impingement jets exiting the ports of said rearward chambers.
an airfoil-shaped, hollow, turbine vane having a leading edge wall, and a trailing edge portion with an exit air slot therein, and pressure and suction sidewalls defining a single internal cavity in communication with said exit air slot;
a single, unitary, air-cooling, hollow insert, of generally complementary airfoil shape in cross section, located in said cavity and extending in a chordwise direc-tion for substantially the entire extent of said cavity;
a plurality of radially extending partition means in said insert dividing the interior thereof into a forward chamber in the leading edge portion of said vane, and at least two separate, successively rearward chambers in communication with each other;
a plurality of impingement ports in the insert walls of all of said chambers;
one radial end portion of said chambers being in communication with a source of cooling air;
means for throttling the flow into said rearward chambers so that said forward chamber is at a relatively higher pressure than said rearward chambers and so the impingement jets through said ports of said forward chamber against said interior vane walls of said leading edge portion are at the significantly higher velocity than the impingement jets exiting the ports of said rearward chambers.
2. The combination according to claim 1 wherein:
said impingement ports in said forward chamber are more widely spaced than the majority of the impingement ports in said rearward chambers.
said impingement ports in said forward chamber are more widely spaced than the majority of the impingement ports in said rearward chambers.
3. The combination of claim 1 wherein:
said throttling means includes a radially out-wardly extending portion of the insert at the radially outer ends of said rearward chambers, and a plurality of throttling holes in said portion of said insert.
said throttling means includes a radially out-wardly extending portion of the insert at the radially outer ends of said rearward chambers, and a plurality of throttling holes in said portion of said insert.
4. The combination of claim 1 wherein:
said rearward chambers comprise at least three chambers.
said rearward chambers comprise at least three chambers.
5. The combination of claim 1 wherein:
said partition means comprises rigidly extending ribs, the first rib separating said forward chamber from the first successively rear chamber being imperforate, and successive rearward second ribs having openings therein.
said partition means comprises rigidly extending ribs, the first rib separating said forward chamber from the first successively rear chamber being imperforate, and successive rearward second ribs having openings therein.
6. The combination of claim 5 wherein:
said second ribs extend radially outwardly less than said first rib so that said rearward chambers are in open communication with each other in their radially outer portions.
said second ribs extend radially outwardly less than said first rib so that said rearward chambers are in open communication with each other in their radially outer portions.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US67184684A | 1984-11-15 | 1984-11-15 | |
| US671,846 | 1984-11-15 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1221915A true CA1221915A (en) | 1987-05-19 |
Family
ID=24696102
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000495185A Expired CA1221915A (en) | 1984-11-15 | 1985-11-13 | Multi-chamber airfoil cooling insert for turbine vane |
Country Status (9)
| Country | Link |
|---|---|
| EP (1) | EP0182588B1 (en) |
| JP (1) | JPS61126302A (en) |
| KR (1) | KR860004224A (en) |
| CN (1) | CN1004291B (en) |
| CA (1) | CA1221915A (en) |
| DE (1) | DE3565298D1 (en) |
| IN (1) | IN163070B (en) |
| IT (1) | IT1186049B (en) |
| MX (1) | MX161444A (en) |
Families Citing this family (30)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2189553B (en) * | 1986-04-25 | 1990-05-23 | Rolls Royce | Cooled vane |
| US5212940A (en) * | 1991-04-16 | 1993-05-25 | General Electric Company | Tip clearance control apparatus and method |
| US5207556A (en) * | 1992-04-27 | 1993-05-04 | General Electric Company | Airfoil having multi-passage baffle |
| US6183192B1 (en) * | 1999-03-22 | 2001-02-06 | General Electric Company | Durable turbine nozzle |
| DE10004128B4 (en) | 2000-01-31 | 2007-06-28 | Alstom Technology Ltd. | Air-cooled turbine blade |
| US6652220B2 (en) * | 2001-11-15 | 2003-11-25 | General Electric Company | Methods and apparatus for cooling gas turbine nozzles |
| US6609880B2 (en) * | 2001-11-15 | 2003-08-26 | General Electric Company | Methods and apparatus for cooling gas turbine nozzles |
| US7008185B2 (en) * | 2003-02-27 | 2006-03-07 | General Electric Company | Gas turbine engine turbine nozzle bifurcated impingement baffle |
| US7871246B2 (en) * | 2007-02-15 | 2011-01-18 | Siemens Energy, Inc. | Airfoil for a gas turbine |
| CN104088673B (en) * | 2008-11-07 | 2016-03-09 | 三菱日立电力系统株式会社 | turbine blade |
| CN101825115B (en) * | 2010-03-31 | 2011-09-28 | 北京航空航天大学 | Blade with built-in bed frame-type pneumatic damping device |
| US20130104567A1 (en) * | 2011-10-31 | 2013-05-02 | Douglas Gerard Konitzer | Method and apparatus for cooling gas turbine rotor blades |
| US9004866B2 (en) * | 2011-12-06 | 2015-04-14 | Siemens Aktiengesellschaft | Turbine blade incorporating trailing edge cooling design |
| US9506351B2 (en) * | 2012-04-27 | 2016-11-29 | General Electric Company | Durable turbine vane |
| EP2706195A1 (en) * | 2012-09-05 | 2014-03-12 | Siemens Aktiengesellschaft | Impingement tube for gas turbine vane with a partition wall |
| EP3189213A1 (en) | 2014-09-04 | 2017-07-12 | Siemens Aktiengesellschaft | Internal cooling system with insert forming nearwall cooling channels in an aft cooling cavity of a gas turbine airfoil |
| GB201417476D0 (en) | 2014-10-03 | 2014-11-19 | Rolls Royce Plc | Internal cooling of engine components |
| US10329932B2 (en) * | 2015-03-02 | 2019-06-25 | United Technologies Corporation | Baffle inserts |
| US9849510B2 (en) | 2015-04-16 | 2017-12-26 | General Electric Company | Article and method of forming an article |
| US9976441B2 (en) | 2015-05-29 | 2018-05-22 | General Electric Company | Article, component, and method of forming an article |
| US9850763B2 (en) | 2015-07-29 | 2017-12-26 | General Electric Company | Article, airfoil component and method for forming article |
| US10253986B2 (en) | 2015-09-08 | 2019-04-09 | General Electric Company | Article and method of forming an article |
| US10087776B2 (en) | 2015-09-08 | 2018-10-02 | General Electric Company | Article and method of forming an article |
| US10739087B2 (en) * | 2015-09-08 | 2020-08-11 | General Electric Company | Article, component, and method of forming an article |
| US10655477B2 (en) | 2016-07-26 | 2020-05-19 | General Electric Company | Turbine components and method for forming turbine components |
| US10400608B2 (en) * | 2016-11-23 | 2019-09-03 | General Electric Company | Cooling structure for a turbine component |
| US10260363B2 (en) | 2016-12-08 | 2019-04-16 | General Electric Company | Additive manufactured seal for insert compartmentalization |
| US10494948B2 (en) * | 2017-05-09 | 2019-12-03 | General Electric Company | Impingement insert |
| US10480347B2 (en) * | 2018-01-18 | 2019-11-19 | United Technologies Corporation | Divided baffle for components of gas turbine engines |
| US10697309B2 (en) | 2018-04-25 | 2020-06-30 | Raytheon Technologies Corporation | Platform cover plates for gas turbine engine components |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2873944A (en) * | 1952-09-10 | 1959-02-17 | Gen Motors Corp | Turbine blade cooling |
| FR1177035A (en) * | 1957-05-28 | 1959-04-20 | Snecma | Method and device for cooling machine parts |
| US3540810A (en) * | 1966-03-17 | 1970-11-17 | Gen Electric | Slanted partition for hollow airfoil vane insert |
| US3891348A (en) * | 1972-04-24 | 1975-06-24 | Gen Electric | Turbine blade with increased film cooling |
| GB1587401A (en) * | 1973-11-15 | 1981-04-01 | Rolls Royce | Hollow cooled vane for a gas turbine engine |
| CH584346A5 (en) * | 1974-11-08 | 1977-01-31 | Bbc Sulzer Turbomaschinen | |
| US4297077A (en) * | 1979-07-09 | 1981-10-27 | Westinghouse Electric Corp. | Cooled turbine vane |
-
1985
- 1985-10-22 IN IN755/CAL/85A patent/IN163070B/en unknown
- 1985-10-24 MX MX375A patent/MX161444A/en unknown
- 1985-11-07 JP JP60248171A patent/JPS61126302A/en active Granted
- 1985-11-11 IT IT8522785A patent/IT1186049B/en active
- 1985-11-13 DE DE8585308230T patent/DE3565298D1/en not_active Expired
- 1985-11-13 EP EP85308230A patent/EP0182588B1/en not_active Expired
- 1985-11-13 CA CA000495185A patent/CA1221915A/en not_active Expired
- 1985-11-14 CN CN85108282.3A patent/CN1004291B/en not_active Expired
- 1985-11-15 KR KR1019850008558A patent/KR860004224A/en not_active Application Discontinuation
Also Published As
| Publication number | Publication date |
|---|---|
| JPH0379522B2 (en) | 1991-12-19 |
| EP0182588A1 (en) | 1986-05-28 |
| DE3565298D1 (en) | 1988-11-03 |
| CN85108282A (en) | 1986-08-27 |
| IT8522785A0 (en) | 1985-11-11 |
| JPS61126302A (en) | 1986-06-13 |
| IN163070B (en) | 1988-08-06 |
| IT1186049B (en) | 1987-11-18 |
| CN1004291B (en) | 1989-05-24 |
| MX161444A (en) | 1990-09-27 |
| KR860004224A (en) | 1986-06-18 |
| EP0182588B1 (en) | 1988-09-28 |
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