CN106014496A - Turbine guide blade adopting rotation straight-line hole passageway closed type cooling structure - Google Patents
Turbine guide blade adopting rotation straight-line hole passageway closed type cooling structure Download PDFInfo
- Publication number
- CN106014496A CN106014496A CN201610510695.7A CN201610510695A CN106014496A CN 106014496 A CN106014496 A CN 106014496A CN 201610510695 A CN201610510695 A CN 201610510695A CN 106014496 A CN106014496 A CN 106014496A
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- China
- Prior art keywords
- array hole
- hole
- suction surface
- straight
- pressure face
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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
- F01D9/04—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
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention belongs to the technical field of gas turbine devices, and particularly relates to a turbine guide blade adopting a rotation straight-line hole passageway closed type cooling structure. The turbine guide blade comprises a blade type pressure face, a blade type suction surface, an upper edge plate and a lower edge plate. The top of the outer side of the upper edge plate is provided with an upper rotation cavity and exhaust guide pipes. The bottom of the outer side of the lower edge plate is provided with a lower rotation cavity and gas inlet guide pipes. A first set of straight-line holes, a second set of straight-line holes and a third set of straight-line holes are formed in the blade type pressure face and the blade type suction surface. The first set of straight-line holes include the front edge straight-line hole, the first pressure face straight-line holes and the first suction surface straight-line holes. The second set of straight-line holes include the second pressure face straight-line holes and the second suction surface straight-line holes. The third set of straight-line holes include the third pressure face straight-line holes, the third suction surface straight-line holes, the blade inner cavity rear straight-line holes and a tail edge passageway. A ventilation hole is formed in the upper edge plate. The turbine guide blade is simple in structure, reasonable in design, high in cold gas utilization rate, efficient, capable of saving energy, safe and environment-friendly.
Description
Technical field:
The invention belongs to gas-turbine plant technical field, be specifically related to a kind of turborotor using the revolution closed cooling structure of hole path in upright arrangement.
Background technology:
Gas turbine is the device that the heat energy of high temperature, high-pressure combustion gas is converted into mechanical energy, and turborotor, as contacting the parts of high-temperature fuel gas in gas turbine at first, is operated in high heat load environment, needs effectively to cool down it.Along with gas turbine technology development, it is more and more faster that turbine inlet temperature (TIT) improves speed, poor owing to newly developing the heat-carrying character of the difficulty of material cooling working medium-air increasing, traditional, use steam cooling technology can relatively well make up air cooled shortcoming.On the one hand the big thermal capacitance of water vapour, the physical property of high thermal conductivity are more suitable for cooling, and on the other hand, the application of steam cooling technology can reduce cooling air consumption, are conducive to improving thermal efficiency of gas turbine, reducing the pollutant emissions such as NOx.
Invention
Content:
In place of the present invention makes up and improves above-mentioned the deficiencies in the prior art, provide a kind of simple in construction, reasonable in design, cold air utilization rate is high, energy-efficient, a kind of turborotor using the revolution closed cooling structure of hole path in upright arrangement of safety and environmental protection, can promote on a large scale and use.
The technical solution used in the present invention is: a kind of turborotor using the revolution closed cooling structure of hole path in upright arrangement, the blade profile leading edge having a common boundary with blade profile suction surface including blade profile pressure face, blade profile suction surface, blade profile pressure face and blade profile trailing edge, supramarginal plate and inframarginal, top outside supramarginal plate is provided with upper rotary chamber and exhaust manifolds, and inframarginal exterior bottom is provided with lower turned cavities and air induction conduit；Described blade profile pressure face and blade profile suction surface are provided with first group of array hole, second group of array hole and the 3rd group of array hole；First group of array hole includes leading edge array hole, the first pressure face array hole and the first suction surface array hole, and wherein the quantity in leading edge array hole is 1, and the quantity in the first pressure face array hole and the first suction surface array hole is all higher than 1；Second group of array hole includes the second pressure face array hole and the second suction surface array hole, and the quantity in the second pressure face array hole and the second suction surface array hole is all higher than 1；3rd group of array hole includes the 3rd pressure face array hole, the 3rd suction surface array hole, array hole, blade inner chamber rear portion and trailing edge passage, and wherein the quantity in the 3rd pressure face array hole, the 3rd suction surface array hole and array hole, blade inner chamber rear portion is all higher than 1；Described supramarginal plate is provided with passage.
Quantity and the position distribution of described air induction conduit are consistent with first group of array hole；Quantity and the position distribution of described exhaust manifolds are consistent with the 3rd group of array hole.
Described upper rotary chamber and the overall dimensions of lower turned cavities and profile and corresponding blade profile pressure face and the overall dimensions at blade profile suction surface position and profile are consistent.
The inner orifice edge of described air induction conduit is provided with 45 degree of straight chamferings.
Described trailing edge passage is wedge-shaped design.
Beneficial effects of the present invention: simple in construction, reasonable in design, cold air utilization rate is high, energy-efficient, safety and environmental protection, it is easy to promote on a large scale and use.Enclosed cooling structure turborotor for steam Cooling Design, in order to reduce blade working temperature, circular in a large number in blade wall indoor design and there is certain cooling array hole distorting rule, this makes blade construction simple, it is prone to processing and manufacturing, and by top turned cavities and bottom turned cavities, all holes in upright arrangement are divided into three groups, therefore structure cold air flows to fixing, cold air utilization rate height and flow losses are little, define the enclosed cooling structure blade of single import, single outlet and combustion gas and cold air path isolation, improve cold air utilization rate；Upper rotary chamber has certain distortion rule as lower turned cavities, upper rotary chamber two side walls is along pressure face and the extension outside supramarginal plate of the suction surface blade profile, lower turned cavities two side walls is along pressure face and the extension outside inframarginal of the suction surface blade profile, so can preferably comply with cold air flow reasonable in design, energy-efficient, safety and environmental protection.
Accompanying drawing illustrates:
Fig. 1 is the three dimensional structure schematic diagram of the present invention.
Fig. 2 is the backsight postrotational three dimensional structure schematic diagram of Fig. 1.
Fig. 3 is that the A of Fig. 1 is to structural representation.
Fig. 4 is the B-B sectional structure schematic diagram of Fig. 1.
Fig. 5 is the cooling steam flow schematic diagram of the present invention.
Detailed description of the invention:
With reference to each figure, a kind of turborotor using the revolution closed cooling structure of hole path in upright arrangement, the blade profile leading edge 3 having a common boundary with blade profile suction surface 2 including blade profile pressure face 1, blade profile suction surface 2, blade profile pressure face 1 and blade profile trailing edge 4, supramarginal plate 5 and inframarginal 6, top outside supramarginal plate 5 is provided with upper rotary chamber 7 and exhaust manifolds 10, and inframarginal 6 exterior bottom is provided with lower turned cavities 8 and air induction conduit 9；Described blade profile pressure face 1 and blade profile suction surface 2 are provided with array hole 12,11, second group of first group of array hole and the 3rd group of array hole 13；First group of array hole 11 includes the 14, first pressure face array hole, leading edge array hole 15 and the first suction surface array hole 16, and wherein the quantity in leading edge array hole 14 is 1, and the quantity in the first pressure face array hole 15 and the first suction surface array hole 16 is all higher than 1；Second group of array hole 12 includes the second pressure face array hole 17 and the second suction surface array hole 18, and the quantity in the second pressure face array hole 17 and the second suction surface array hole 18 is all higher than 1；3rd group of array hole 13 includes the 3rd suction surface array hole 20, pressure face array hole the 19, the 3rd, array hole, blade inner chamber rear portion 21 and trailing edge passage 22, and wherein the quantity in the 3rd suction surface array hole 20, pressure face array hole the 19, the 3rd and array hole, blade inner chamber rear portion 21 is all higher than 1；Described supramarginal plate 5 is provided with passage 23；Quantity and the position distribution of described air induction conduit 9 are consistent with first group of array hole 11；Quantity and the position distribution of described exhaust manifolds 10 are consistent with the 3rd group of array hole 13；Described upper rotary chamber 7 and the overall dimensions of lower turned cavities 8 and profile and corresponding blade profile pressure face 1 and the overall dimensions at blade profile suction surface 2 position and profile are consistent；The inner orifice edge of described air induction conduit 9 is provided with 45 degree of straight chamferings；Described trailing edge passage 22 is wedge-shaped design.
nullAir-flow is entered after blade through by first group of array hole 11 by air induction conduit 9，After bucket front is carried out convection current cooling，Flow into the upper rotary chamber 7 at top，Form gas rotary current 25，Flow into second group of array hole 12，After carrying out convection current cooling in the middle part of blade，Lower turned cavities 8 through bottom，Form gas rotary current 26，Flow into the 3rd group of array hole，After bucket rear and afterbody are carried out convection current cooling，Discharged by vane tip exhaust manifolds 10，Often in group hole, gas flow is fixed，Finally flowed out by vane tip exhaust manifolds 10，Thereby determine that the stream of whole cooling steam，Define single import、The enclosed cooling structure blade that single outlet and combustion gas are isolated with cold air path，Improve cold air utilization rate，Blade internal face can form closing chamber at，In order to avoid dead space occurs，Passage 23 is had at blade supramarginal plate；Hole in upright arrangement has certain distortion rule, be cross section be circular cooling designated lane, through blade blade, supramarginal plate 5 and inframarginal 6, hole bearing of trend and blade exterior fuel gas flow direction near vertical；Upper rotary chamber 7 and lower turned cavities 8 have certain distortion rule equally, upper rotary chamber 7 two side walls is along pressure face and the extension outside supramarginal plate of the suction surface blade profile, lower turned cavities 8 two side walls is along pressure face and the extension outside inframarginal of the suction surface blade profile, so can preferably comply with cold air flow.
Supramarginal plate 5 is used for being mounted and fixed on Gas Turbine casing, and hole in upright arrangement is between blade outside wall surface and internal face, and wherein edge and blade profile inwall end aperture are relatively large, are provided with wedge shape cooling duct at trailing edge.There is cavity at it addition, be positioned at blade profile inwall and upper inframarginal inwall, in order to avoid forming dead space, cavity top supramarginal plate side is at least provided with passage at.The wall of blade profile is at least arranged a hole in upright arrangement, hole in upright arrangement is the circular hole passage of the supramarginal plate 6 of inframarginal 5, blade and the blade of through blade in blade profile wall, for through-flow cooling steam, according to blade profile wall thickness, carry out Cooling Holes quantity, the design of distribution in upright arrangement；In hole in upright arrangement, at least one has distortion rule radially, distortion rule is from blade profile exterior design, it is positioned at the aperture, hole in upright arrangement of blade inlet edge more than the aperture, hole in upright arrangement on blade pressure surface and suction surface, equally, being positioned at blade trailing edge position, the hole in upright arrangement at blade inner chamber rear portion, at least an aperture is more than the aperture, hole in upright arrangement on blade pressure surface and suction surface.Described trailing edge wedge shape cooling duct, as the flow region of end cooling steam, is positioned at the trailing edge position of blade, inframarginal and blade on penetrating blade, has distortion rule radially, and distortion rule is from blade profile exterior design.Upper rotary chamber 7 and lower turned cavities 8 are suitable for blade design, and both sides profile is blade profile pressure face 1 and the extension of blade profile suction surface 2 listrium up and down, in conjunction with top cover and bead plate, are encircled into upper rotary chamber 7 and lower turned cavities 8.From cold air flow direction, upper rotary chamber 7 is for turning round the airflow direction in first group of air inlet array hole, air-flow after revolution flows into lower turned cavities 8 through second group of array hole, after airflow direction is turned round by lower turned cavities 8 again, blade is discharged by supramarginal plate 5 top, often including at least a hole in upright arrangement being positioned at blade profile pressure face and a hole in upright arrangement being positioned at blade profile suction surface in group hole in upright arrangement through the 3rd group of array hole.Comprising at least one air induction conduit 9 bottom blade inframarginal 6, all air induction conduit 9 tops are in a radial height position；Blade supramarginal plate 5 top comprises at least one exhaust manifolds 10, and all exhaust manifolds 10 tops are in a radial height position.
Turborotor is used for realizing the steam cooling of gas turbine high temperature turbo blade, cooling steam enters the hole in upright arrangement within blade profile wall by blade bottom air induction conduit 9, blade wall is cooled down by the type of cooling using convection current, it is divided into three groups by cooling down hole in upright arrangement in a large number by upper rotary chamber 7 and lower turned cavities 8, often in group hole, gas flow is fixed, finally flowed out by vane tip exhaust manifolds 10, thereby determine that the stream of whole cooling steam, define single import, the enclosed cooling structure blade that single outlet and combustion gas are isolated with cold air path, improve cold air utilization rate.The simple in construction of the present invention, reasonable in design, cold air utilization rate is high, energy-efficient, safety and environmental protection, it is easy to promote on a large scale and use.
Claims (5)
1. the turborotor using the revolution closed cooling structure of hole path in upright arrangement, the blade profile leading edge (3) having a common boundary with blade profile suction surface (2) including blade profile pressure face (1), blade profile suction surface (2), blade profile pressure face (1) and blade profile trailing edge (4), supramarginal plate (5) and inframarginal (6), it is characterized in that: the top in supramarginal plate (5) outside is provided with upper rotary chamber (7) and exhaust manifolds (10), and inframarginal (6) exterior bottom is provided with lower turned cavities (8) and air induction conduit (9)；Described blade profile pressure face (1) and blade profile suction surface (2) are provided with first group of array hole (11), second group of array hole (12) and the 3rd group of array hole (13)；First group of array hole (11) includes leading edge array hole (14), the first pressure face array hole (15) and the first suction surface array hole (16), wherein the quantity of leading edge array hole (14) is 1, and the quantity in the first pressure face array hole (15) and the first suction surface array hole (16) is all higher than 1；Second group of array hole (12) includes the second pressure face array hole (17) and the second suction surface array hole (18), and the quantity in the second pressure face array hole (17) and the second suction surface array hole (18) is all higher than 1；3rd group of array hole (13) includes the 3rd pressure face array hole (19), the 3rd suction surface array hole (20), array hole, blade inner chamber rear portion (21) and trailing edge passage (22), and wherein the quantity at the 3rd pressure face array hole (19), the 3rd suction surface array hole (20) and array hole, blade inner chamber rear portion (21) is all higher than 1；Described supramarginal plate (5) is provided with passage (23).
A kind of turborotor using the revolution closed cooling structure of hole path in upright arrangement the most according to claim 1, it is characterised in that: quantity and the position distribution of described air induction conduit (9) are consistent with first group of array hole (11)；Quantity and the position distribution of described exhaust manifolds (10) are consistent with the 3rd group of array hole (13).
A kind of turborotor using the revolution closed cooling structure of hole path in upright arrangement the most according to claim 1, it is characterised in that: described upper rotary chamber (7) and the overall dimensions of lower turned cavities (8) and profile and corresponding blade profile pressure face (1) and the overall dimensions at blade profile suction surface (2) position and profile are consistent.
A kind of turborotor using the revolution closed cooling structure of hole path in upright arrangement the most according to claim 1, it is characterised in that: the inner orifice edge of described air induction conduit (9) is provided with 45 degree of straight chamferings.
A kind of turborotor using the revolution closed cooling structure of hole path in upright arrangement the most according to claim 1, it is characterised in that: described trailing edge passage (22) is wedge-shaped design.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2016101936323 | 2016-03-31 | ||
| CN201610193632.3A CN105649683A (en) | 2016-03-31 | 2016-03-31 | Turbine guide vane of rotary in-line hole channel closed type cooling structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106014496A true CN106014496A (en) | 2016-10-12 |
Family
ID=56496868
Family Applications (3)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610193632.3A Withdrawn CN105649683A (en) | 2016-03-31 | 2016-03-31 | Turbine guide vane of rotary in-line hole channel closed type cooling structure |
| CN201610510695.7A Pending CN106014496A (en) | 2016-03-31 | 2016-07-04 | Turbine guide blade adopting rotation straight-line hole passageway closed type cooling structure |
| CN201620684914.9U Active CN205805624U (en) | 2016-03-31 | 2016-07-04 | A kind of turborotor using the revolution closed cooling structure of hole path in upright arrangement |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610193632.3A Withdrawn CN105649683A (en) | 2016-03-31 | 2016-03-31 | Turbine guide vane of rotary in-line hole channel closed type cooling structure |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620684914.9U Active CN205805624U (en) | 2016-03-31 | 2016-07-04 | A kind of turborotor using the revolution closed cooling structure of hole path in upright arrangement |
Country Status (1)
| Country | Link |
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| CN (3) | CN105649683A (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105649683A (en) * | 2016-03-31 | 2016-06-08 | 中国船舶重工集团公司第七�三研究所 | Turbine guide vane of rotary in-line hole channel closed type cooling structure |
| CN110295956A (en) * | 2019-08-09 | 2019-10-01 | 上海电气燃气轮机有限公司 | A kind of split type turbine nozzle blade |
| CN113931702A (en) * | 2020-06-29 | 2022-01-14 | 中国航发商用航空发动机有限责任公司 | Gas turbine, guide vane and guide vane edge plate thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004137958A (en) * | 2002-10-17 | 2004-05-13 | Mitsubishi Heavy Ind Ltd | Gas turbine rotor blade |
| US7198458B2 (en) * | 2004-12-02 | 2007-04-03 | Siemens Power Generation, Inc. | Fail safe cooling system for turbine vanes |
| US8328518B2 (en) * | 2009-08-13 | 2012-12-11 | Siemens Energy, Inc. | Turbine vane for a gas turbine engine having serpentine cooling channels |
| US8511968B2 (en) * | 2009-08-13 | 2013-08-20 | Siemens Energy, Inc. | Turbine vane for a gas turbine engine having serpentine cooling channels with internal flow blockers |
| CN205805624U (en) * | 2016-03-31 | 2016-12-14 | 中国船舶重工集团公司第七�三研究所 | A kind of turborotor using the revolution closed cooling structure of hole path in upright arrangement |
-
2016
- 2016-03-31 CN CN201610193632.3A patent/CN105649683A/en not_active Withdrawn
- 2016-07-04 CN CN201610510695.7A patent/CN106014496A/en active Pending
- 2016-07-04 CN CN201620684914.9U patent/CN205805624U/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004137958A (en) * | 2002-10-17 | 2004-05-13 | Mitsubishi Heavy Ind Ltd | Gas turbine rotor blade |
| US7198458B2 (en) * | 2004-12-02 | 2007-04-03 | Siemens Power Generation, Inc. | Fail safe cooling system for turbine vanes |
| US8328518B2 (en) * | 2009-08-13 | 2012-12-11 | Siemens Energy, Inc. | Turbine vane for a gas turbine engine having serpentine cooling channels |
| US8511968B2 (en) * | 2009-08-13 | 2013-08-20 | Siemens Energy, Inc. | Turbine vane for a gas turbine engine having serpentine cooling channels with internal flow blockers |
| CN205805624U (en) * | 2016-03-31 | 2016-12-14 | 中国船舶重工集团公司第七�三研究所 | A kind of turborotor using the revolution closed cooling structure of hole path in upright arrangement |
Also Published As
| Publication number | Publication date |
|---|---|
| CN205805624U (en) | 2016-12-14 |
| CN105649683A (en) | 2016-06-08 |
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20161012 |
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| RJ01 | Rejection of invention patent application after publication |