CN105649683A - Turbine guide vane of rotary in-line hole channel closed type cooling structure - Google Patents
Turbine guide vane of rotary in-line hole channel closed type cooling structure Download PDFInfo
- Publication number
- CN105649683A CN105649683A CN201610193632.3A CN201610193632A CN105649683A CN 105649683 A CN105649683 A CN 105649683A CN 201610193632 A CN201610193632 A CN 201610193632A CN 105649683 A CN105649683 A CN 105649683A
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- CN
- China
- Prior art keywords
- array hole
- hole
- line hole
- pressure face
- blade profile
- 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.)
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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 equipment, and particularly relates to a turbine guide vane of a rotary in-line hole channel closed type cooling structure. The turbine guide vane comprises a blade profile pressure face, a blade profile suction face, an upper marginal plate and a lower marginal plate. The top of the outer side of the upper marginal plate is provided with an upper rotary cavity and an exhaust guide pipe. The bottom of the outer side of the lower marginal plate is provided with a lower rotary cavity and an air inlet guide pipe. The blade profile pressure face and the blade profile suction face are provided with a first in-line hole set, a second in-line hole set and a third in-line hole set. The first in-line hole set comprises a front marginal in-line hole, a first pressure face in-line hole and a first suction face in-line hole. The second in-line hole set comprises a second pressure face in-line hole and a second suction face in-line hole. The third in-line hole set comprises a third pressure face in-line hole, a third suction face in-line hole, a blade inner cavity rear in-line hole and a tail marginal channel. The upper marginal plate is provided with an air hole. The turbine guide vane is simple in structure, reasonable in design, high in cool air utilization rate, energy-efficient, safe and environmentally friendly.
Description
Technical field:
The invention belongs to gas-turbine plant technical field, be specifically related to a kind of turborotor adopting 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 the parts contacting high-temperature fuel gas in gas turbine at first, is operated in high heat load environment, it is necessary to it is cooled down effectively. Along with gas turbine technology development, it is more and more faster that turbine inlet temperature (TIT) improves speed, the heat-carrying character of the difficulty cooling working medium-air increasing, traditional owing to newly developing material is poor, adopts steam cooling technology can relatively well make up air cooled shortcoming. On the one hand the big thermal capacitance of water vapour, high thermal conductivity physical property be more suitable for cooling, on the other hand, the application of steam cooling technology can reduce cooling air consumption, is conducive to improving thermal efficiency of gas turbine, reducing the pollutant emissions such as NOx.
Summary of the invention:
The present invention makes up and improves above-mentioned the deficiencies in the prior art part, provide a kind of simple in construction, reasonable in design, cold air utilization rate is high, energy-efficient, a kind of turborotor adopting the revolution closed cooling structure of hole path in upright arrangement of safety and environmental protection, it is possible to promotes on a large scale and uses.
The technical solution used in the present invention is: a kind of turborotor adopting the revolution closed cooling structure of hole path in upright arrangement, the blade profile leading edge having a common boundary including blade profile pressure face, blade profile suction surface, blade profile pressure face and blade profile suction surface 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.
The quantity of described air induction conduit and position distribution are consistent with first group of array hole; The quantity of described exhaust manifolds and position distribution are consistent with the 3rd group of array hole.
Described upper rotary chamber is consistent with the overall dimensions at corresponding blade profile pressure face and blade profile suction surface position and profile with the overall dimensions of lower turned cavities and profile.
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 promotes on a large scale and uses. Enclosed cooling structure turborotor for steam Cooling Design, in order to reduce blade working temperature, in blade wall indoor design circle in a large number the cooling array hole with certain distortion 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 the structure cold air flow direction is fixing, cold air utilization rate is high and flow losses are little, define single import, single outlet and combustion gas and the enclosed cooling structure blade of cold air path isolation, improve cold air utilization rate; Upper rotary chamber is same with lower turned cavities has certain distortion rule, upper rotary chamber two side walls is along pressure face and suction surface blade profile to the extension outside supramarginal plate, lower turned cavities two side walls is along pressure face and suction surface blade profile to the extension outside inframarginal, so can comply with cold air flow better 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 postrotational three dimensional structure schematic diagram of backsight 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 adopting the revolution closed cooling structure of hole path in upright arrangement, the blade profile leading edge 3 having a common boundary including blade profile pressure face 1, blade profile suction surface 2, blade profile pressure face 1 and blade profile suction surface 2 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; The quantity of described air induction conduit 9 and position distribution are consistent with first group of array hole 11; The quantity of described exhaust manifolds 10 and position distribution are consistent with the 3rd group of array hole 13; Described upper rotary chamber 7 is consistent with the overall dimensions at corresponding blade profile pressure face 1 and blade profile suction surface 2 position and profile with the overall dimensions of lower turned cavities 8 and profile; 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.
Air-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, single outlet and combustion gas and the isolated enclosed cooling structure blade of cold air path, improve cold air utilization rate, blade internal face can form a place and close chamber, in order to avoid dead space occurs, passage 23 is had at blade supramarginal plate place, hole in upright arrangement has certain distortion rule, to 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 suction surface blade profile to the extension outside supramarginal plate, lower turned cavities 8 two side walls is along pressure face and suction surface blade profile to the extension outside inframarginal, so can comply with cold air flow better.
Supramarginal plate 5 is 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, and trailing edge place is provided with a wedge shape cooling duct, place. It addition, be positioned at blade profile inwall and upper inframarginal inwall place exists place's cavity, in order to avoid forming dead space, cavity top supramarginal plate side is at least provided with place's passage. 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 the inframarginal 5 of through blade in blade profile wall, blade and blade, for through-flow cooling steam, according to blade profile wall thickness, carry out the design of Cooling Holes quantity in upright arrangement, distribution; 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, it is positioned at the hole in upright arrangement at blade trailing edge position, blade inner chamber rear portion, has at least an aperture 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 a 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 gone out by supramarginal plate 5 top row, 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 adopting 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, single outlet and combustion gas and the isolated enclosed cooling structure blade of 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 promotes on a large scale and uses.
Claims (5)
1. the turborotor adopting the revolution closed cooling structure of hole path in upright arrangement, the blade profile leading edge (3) having a common boundary including blade profile pressure face (1), blade profile suction surface (2), blade profile pressure face (1) and blade profile suction surface (2) 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).
2. a kind of turborotor adopting the revolution closed cooling structure of hole path in upright arrangement according to claim 1, it is characterised in that: the quantity of described air induction conduit (9) and position distribution are consistent with first group of array hole (11); The quantity of described exhaust manifolds (10) and position distribution are consistent with the 3rd group of array hole (13).
3. a kind of turborotor adopting the revolution closed cooling structure of hole path in upright arrangement according to claim 1, it is characterised in that: described upper rotary chamber (7) is consistent with overall dimensions and the profile of corresponding blade profile pressure face (1) and blade profile suction surface (2) position with the overall dimensions of lower turned cavities (8) and profile.
4. a kind of turborotor adopting the revolution closed cooling structure of hole path in upright arrangement 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.
5. a kind of turborotor adopting the revolution closed cooling structure of hole path in upright arrangement according to claim 1, it is characterised in that: described trailing edge passage (22) is wedge-shaped design.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610193632.3A CN105649683A (en) | 2016-03-31 | 2016-03-31 | Turbine guide vane of rotary in-line hole channel closed type cooling structure |
| CN201610510695.7A CN106014496A (en) | 2016-03-31 | 2016-07-04 | Turbine guide blade adopting rotation straight-line hole passageway closed type cooling structure |
| CN201620684914.9U CN205805624U (en) | 2016-03-31 | 2016-07-04 | A kind of turborotor using the revolution closed cooling structure of hole path in upright arrangement |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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 |
|---|---|
| CN105649683A true CN105649683A (en) | 2016-06-08 |
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 After (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| 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 |
Country Status (1)
| Country | Link |
|---|---|
| CN (3) | CN105649683A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Families Citing this family (2)
| 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 |
| 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 |
Family Cites Families (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 |
| 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 |
| US8328518B2 (en) * | 2009-08-13 | 2012-12-11 | Siemens Energy, Inc. | Turbine vane for a gas turbine engine having serpentine cooling channels |
| 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 |
-
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
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN205805624U (en) | 2016-12-14 |
| CN106014496A (en) | 2016-10-12 |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C04 | Withdrawal of patent application after publication (patent law 2001) | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20160608 |