CN204312137U - Turbogenerator and turbomachine injection nozzle wheel blade section - Google Patents
Turbogenerator and turbomachine injection nozzle wheel blade section Download PDFInfo
- Publication number
- CN204312137U CN204312137U CN201420578804.5U CN201420578804U CN204312137U CN 204312137 U CN204312137 U CN 204312137U CN 201420578804 U CN201420578804 U CN 201420578804U CN 204312137 U CN204312137 U CN 204312137U
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- China
- Prior art keywords
- coolant path
- wheel blade
- radial directed
- wall
- nozzle wheel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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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
- 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
-
- 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
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- 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
- F01D9/06—Fluid supply conduits to nozzles or the like
- F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model discloses a kind of turbogenerator and turbomachine injection nozzle wheel blade section, described turbomachine injection nozzle wheel blade section comprises one or more nozzle wheel blade, described nozzle wheel blade extends between radially inner side wall and outer side wall, each nozzle wheel blade has peripheral edge wall, and described peripheral edge wall extends between the frontier and rear of described wheel blade.In one exemplary embodiment, the coolant path of at least one cardinal principle radial directed is formed in described peripheral edge wall and is positioned at described leading edge place, and the opposite end place of described coolant path has opening.The position of described coolant path and length can change around described peripheral edge wall, and the described inner chamber of described wheel blade can have rib, described rib adjoins described one or more coolant path and extends, to reinforce described wall and provide extra frigorimeter area in described inner chamber along it.The utility model can provide and cool more efficiently.
Description
Technical field
The utility model relates generally to the efficiency and/or operation of improving turbogenerator.Specifically but do not say with not limiting, the utility model relates to the cooling improving turbomachine injection nozzle wheel blade or blade.
Background technique
Gas turbine engine generally includes compressor, one or more burner and at least one turbine section.Described compressor and turbine section generally include axially be stacked at different levels in multirow wheel blade and movable vane.Every one-level can comprise the stator wheel blade of the circumferentially spaced that multirow replaces, and described stator wheel blade is fixing, and the movable vane of circumferentially spaced, and described movable vane is arranged on and is fixed on the wheel of turbine rotor.In operation, the rotor blade in compressor rotates, with the air stream of compressed supply to compressor along with rotor.Most of compressed air mixes with the gas in one or more burner or liquid fuel and lights, and to provide high temperature gas flow, described gas flow expands through the turbine section of motor, causes turbine rotor to rotate.Therefore, energy contained in fuel is converted into the mechanical energy of rotor, for the rotor blade of rotary compressor, thus produces the pressurized air supply needed for burning, and meanwhile, described mechanical energy is also for the coil of rotary generator, thus generating.
In operation, due to the speed of the extreme temperature in high temperature gas passage, working fluid and the rotational speed of motor, therefore rotate movable vane (or fin) and fixed stator wheel blade and all become highly pressurized due to machinery and thermal force.
Those of ordinary skill in affiliated field will be recognized, a kind of strategy alleviating thermal stress is cooling jet wheel blade and/or movable vane, so that the temperature that wheel blade and/or movable vane bear is less than the temperature of high temperature gas passage.Such as, by effective cooling, these high temperature gas passage parts can bear more high ignition temperature, bear larger thermal-mechanical stress and/or increase the service life at high operating temperatures, these turbogenerator all can be made to become more cost is effectively and efficient.A kind of method at run duration cooling wheel blade and movable vane uses internal cooling channel or loop.Usually, this is comprised the lower temperature air can supplied by compressor and is carried through internal cooling loop in wheel blade or fin.
But still need provide more effectively the leading edge etc. of the fixed nozzle wheel blade be exposed in high-temperature combustion gas and cool efficiently, especially in the first turbine stage, in the stage, temperature and the thermal stress of experience are maximum.
Model utility content
The purpose of this utility model is to provide a kind of turbogenerator and turbomachine injection nozzle wheel blade section, and it has the gas turbine airfoils of cooling humidification, to provide high efficiency cooling.
Exemplary but in nonlimiting examples at one, provide a kind of turbomachine injection nozzle wheel blade section, described turbomachine injection nozzle wheel blade section comprises: one or more nozzle wheel blade, described nozzle wheel blade extends between radially inner side wall and radial outside wall, each nozzle wheel blade has edge wall, and described edge wall comprises leading edge and trailing edge; And the coolant path of at least one cardinal principle radial directed, described coolant path is formed in peripheral edge wall, has the entrance being positioned at described madial wall and described one of them side-walls of outer side wall.
As the turbomachine injection nozzle wheel blade section in this embodiment, the coolant path of at least one radial directed wherein said comprises the coolant path of multiple radial directed, and the coolant path of described multiple radial directed comprises a coolant path of the forefront being positioned at described leading edge;
Wherein said nozzle wheel blade hollow, and wherein the rib of radial directed is provided on the internal surface of described peripheral edge wall, adjoins the coolant path of at least one radial directed described and extends along it;
Wherein said nozzle wheel blade hollow, and wherein the rib of radial directed is provided on the internal surface of described peripheral edge wall, adjoins each coolant path in the coolant path of described multiple radial directed and extends along it;
The rib of wherein said radial directed is arranged in the internal cooling cavity of described nozzle wheel blade;
The coolant path of at least one radial directed wherein said comprises multiple coolant path, the spaced position place of described multiple coolant path between described frontier and rear around described peripheral edge wall, and wherein the rib of radial directed is provided on the internal surface of described peripheral edge wall, adjoins each coolant path in described multiple coolant path and extend along it;
The coolant path of wherein said multiple radial directed has outlet, and the Different Diameter between described madial wall and outer side wall is to position;
Wherein each described wheel blade comprises internal cooling loop, the coolant path of described internal cooling circuit and at least one radial directed described is independent and be not connected, and the outlet of at least one path described is arranged in another sidewall of described madial wall and outer side wall;
The coolant path of at least one radial directed wherein said has circle, rectangle or race track shaped cross-section shape;
Wherein the coolant path of at least one radial directed radially length dimension there is the part of multiple different-diameter.
In in another indefiniteness, the utility model provides a kind of turbogenerator, described turbogenerator comprises compressor, at least one burner and at least one turbine stage, described turbine stage comprises a line fixed nozzle wheel blade, described fixed nozzle wheel blade extends between radially inner side wall and radial outside wall, each nozzle wheel blade has peripheral edge wall, and described peripheral edge wall comprises leading edge and trailing edge; And the coolant path of at least one cardinal principle radial directed, described coolant path is formed in peripheral edge wall, has the entrance being positioned at described madial wall and one of them side-walls of outer side wall.
As the turbogenerator in this embodiment, the coolant path of at least one radial directed wherein said comprises the coolant path of multiple radial directed, and the coolant path of described multiple radial directed comprises a coolant path of the forefront being positioned at described leading edge;
Wherein said nozzle wheel blade hollow, and wherein the rib of radial directed is provided on the internal surface of described peripheral edge wall, adjoins the coolant path of at least one radial directed described and extends along it;
Wherein said nozzle wheel blade hollow, and wherein the rib of radial directed is provided on the internal surface of described peripheral edge wall, adjoins each coolant path in the coolant path of described multiple radial directed and extends along it;
The rib of wherein said radial directed is arranged in the internal cooling cavity of described nozzle wheel blade;
The coolant path of at least one radial directed wherein said comprises multiple coolant path, the spaced position place of described multiple coolant path between described frontier and rear around described peripheral edge wall, and wherein the rib of radial directed is provided on the internal surface of described peripheral edge wall, adjoins each coolant path in described multiple coolant path and extend along it;
The coolant path of at least one radial directed wherein said has the outlet being connected to described internal cooling cavity;
Wherein said wheel blade comprises internal cooling loop, and the coolant path of described internal cooling circuit and at least one radial directed described is independent and be not connected, and the outlet of at least one path described is arranged in another sidewall of described madial wall and outer side wall;
The coolant path of at least one radial directed wherein said has circle, rectangle or race track shaped cross-section shape.
Another feature of the present utility model provides strengthening rib in the inner chamber of nozzle wheel blade, and the described path in described strengthening rib and described peripheral edge wall is adjacent and extend along described path at least partly.Therefore, in another illustrative aspects, provide a kind of turbogenerator, described turbogenerator comprises compressor, at least one burner and at least one turbine stage, described turbine stage comprises: a line fixed nozzle wheel blade, described fixed nozzle wheel blade extends between radially inner side wall and outer side wall, and each nozzle wheel blade has peripheral edge wall, and described peripheral edge wall comprises leading edge and trailing edge; And the coolant path of multiple cardinal principle radial directed, described coolant path is included in described leading edge place, formed around described peripheral edge wall, the coolant path of described multiple cardinal principle radial directed extends along the radial length between described madial wall and outer side wall at least partly, and have entrance, described entrance is positioned at inside or the adjoining position place of described madial wall and one of them sidewall of outer side wall; And strengthening rib, each coolant path place of described strengthening rib in the coolant path of contiguous described multiple cardinal principle radial directed extends along the internal surface of described peripheral edge.
The beneficial effects of the utility model are to provide and cool more efficiently.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of conventional gas turbine motor;
Fig. 2 is the partial side view of the turbine section of conventional gas turbine motor;
Fig. 3 is exemplary according to the utility model one but the perspective view of the combustion gas turbine nozzle wheel blade group of non-limiting example;
Fig. 4 is exemplary according to the utility model one but the partial sectional view of the leading edge coolant path of nonlimiting examples;
Fig. 5 and Fig. 6 is the amplification detailed drawing of cutting in Fig. 4;
Fig. 7 is the fragmentary, perspective view of the exemplary coolant path according to an embodiment;
Fig. 8 is the fragmentary, perspective view of the exemplary coolant path according to another embodiment;
Fig. 9 is the fragmentary, perspective view of the exemplary coolant path according to another embodiment;
Figure 10 is exemplary according to another but the partial top view being provided with the nozzle wheel blade of coolant path of nonlimiting examples;
Figure 11 is the partial sectional view with the nozzle wheel blade of the coolant path of different-diameter according to another exemplary embodiment; And
Figure 12 is the partial sectional view of the nozzle wheel blade according to another exemplary embodiment, and described nozzle wheel blade has the coolant path array of the leading edge of contiguous described wheel blade.
Embodiment
Fig. 1 is the schematic diagram of gas turbine system 10, and as described in this specification further, described gas turbine system comprises the fixed blade and rotation blade or movable vane that can be provided with internal cooling loop.Belong in the layout of conventional art this in other, the air supplied by entrance 12 supercharging and lighting with fuel mix in one or more burner 16 in compressor 14, thus produce high-temperature combustion gas.The energy in combustion gas is extracted, to drive the generator 20 for generating electricity in the one or more combustion gas turbine parts 18 being placed in described burner downstream.The energy extracted can also be used for driving compressor 14, note that turbine rotor 22 can be that compressor, turbine stage and generator are common simultaneously.But the utility model described in this specification is not limited in illustrated gas turbine system.In addition with regard to this respect, the cooling loop described in this specification is applicable to the various film cooling structures using the air flowing through cooling loop passage or chamber completely.
In addition see Fig. 2, in typical combustion gas turbine structure, multiple burner 16 can be settled in the form of a ring around turbine rotor, and have multiple transition piece 24, high-temperature combustion gas is transported to combustion gas turbine part 18 from corresponding burner by described transition piece simultaneously.
Combustion gas turbine part 18 as shown in Figure 2 comprises three independent levels.Every one-level comprises one group of movable vane 26,28,30, and it is connected respectively to corresponding rotor wheel 32,34 and 36, and described rotor wheel is attached to turbine rotor or axle (not shown) in a conventional manner.The annular array of stator blade or wheel blade 38,40,42 is respectively equipped with between axially spaced multirow movable vane, described stator blade or wheel blade comprise turbomachine injection nozzle, described turbomachine injection nozzle is fixed to the turbine stator (not shown) of surrounding, and is labeled as S1N, S2N and S3N in fig. 2.
Described row nozzle has madial wall 46 and outer side wall 48, and described mark is only applicable to the wheel blade 38 of described row, but similar madial wall and outer side wall are also relevant to the wheel blade of each nozzle level.Described sidewall is arranged with the form of bow-shaped section usually, so that every section can support one, two or more wheel blades.
Fig. 3 shows according to the first exemplary but wheel blade section of nonlimiting examples of the present utility model.Two wheel blades 50,52 have peripheral edge wall 51,53 respectively, and it extends around described wheel blade, corresponding leading edge 54,56 are connected with trailing edge (is illustrated as 55).Described wheel blade is supported between the madial wall 46 of described section and outer side wall 48.The leading edge 54,56 of nozzle wheel blade 50,52 is exposed to and flows in the high-temperature combustion gas the first turbine stage from transition piece 24.Because wheel blade 50,52 is substantially identical, therefore only need describe one in detail, should be appreciated that, all wheel blades 38 in S1N nozzle all can have following cooling humidification.
Exemplary but in nonlimiting examples, leading edge 54 has the extra air-circulation features independent of other conventional interior cooling loops that can be located in wheel blade at one.Concrete with reference to Fig. 4 to Fig. 6, cooling channel or path 58 are between the radial outer end 60 and radial inner end 62 of wheel blade, and the leading edge 54 along nozzle wheel blade 50 extends diametrically through peripheral edge wall 51.In the shown example, inner 62 outwards extend at side 64 place.Can recognize, path 58 can be holed or is cast in appropriate location, and described path can extend through madial wall 46 and outer side wall 48.Path 58 opens wide at radial outer end and radial inner end place, flows through described passage to allow compressor air-discharging or extracting air.Due in the exemplary embodiment, passage 58 be illustrated as extend in peripheral edge wall 51 wall thickness in, therefore need reinforcement described edge wall, to maintain required thickness, as detailed below.Can recognize there is a coolant path 58 as described in Figure, or multiple coolant path can be had across the leading edge of described wheel blade, and described path can have various sectional shape.
Fig. 7 to Fig. 9 illustrates the example of multiple coolant paths layouts with different cross section shape and inner reinforcing ribs structure.Specifically, Fig. 7 shows the array of three cooling channels or path, comprises the path 58 of the forefront being positioned at leading edge 54, and adjacent path 66 and 68, described path all has " track type " cross section, inner rib 70,72 and 74 and corresponding path general alignment and extend along it.In operation, the cooling twice stream that compressor provides will pass passage or the path 58,66 and 68 of radial directed, reduce leading edge temperature, thus improve LCF, creep and oxidizability.Rib 70,72 and 74 is for reinforcing the wall thickness of the leading edge 54 facing corresponding coolant path.Fig. 8 shows similar layout, but coolant path 158,166 and 168 has circular section shape, and strengthening rib 170,172 and 174 keeps roughly the same with Fig. 7.Fig. 9 shows similar layout, but coolant path 258,266 and 268 has substantially rectangular sectional shape.Equally, similar shown in inner reinforcing ribs 270,272 and 274 and Fig. 7 and Fig. 8.Can recognize, coolant path shape and strengthening rib shape can change as required, to realize required cooling.Such as, described rib tapered or otherwise can have the uneven gauge along its corresponding length.
For Fig. 7, should also be noted that, the existence of leading edge cooling channel 58,66 and 68 does not change can as the existing leading edge cooling chamber 76 of a part for other conventional interior wheel blade cooling loops, but the rib in cooling chamber 76 70,72 and 74 may be used for increasing the surface area in chamber, thus can strengthen cooling.
Can also recognize, quantity and the position of the coolant path arranged in wheel blade peripheral edge wall can change.Such as, as shown in Figure 10, and according to cooling requirement, multiple path 76 can be formed at around in all or part of multiple spaced position of peripheral edge wall 78, and inner reinforcing ribs is set as required, to meet the minimum thickness requirement for peripheral edge wall.
As shown in figure 11, individual channel can be different along the diameter of its corresponding length.Specifically, the coolant path 80 be formed in peripheral edge wall 82 has first diameter parts 84 adjacent with outer side wall 86 and smaller diameter portion 88, in the radial position of described smaller diameter portion between madial wall and outer side wall.Transition point between each diameter can occur as required, specifically depends on cooling requirement.
Figure 12 shows another kind of coolant path and arranges, in this arrangement, the radial length of coolant path is different on every side of leading edge 90.Specifically, diminishing two the extra paths 92 and 94 of radial length are illustrated as being located at the side of leading edge path 96, should be appreciated that, similar path can symmetrical or asymmetric mode be formed on the opposite side of leading edge 90.Therefore, described path can terminate in any position between radially inner side wall and/or outer side wall (such as, 50% to 100% of the radial length of wheel blade), and each path can have one or more outlet of the internal cooling cavity be connected in wheel blade.In fig. 12, leading edge path 96 is illustrated as has multiple outlet 98, and this feature goes for any coolant path layout described in this specification.Note that outlet 98 or can cannot extend through strengthening rib (not shown in Figure 12).
In addition, the direction of two stage compressor exhaust or extraction air-flow can be radially outward or radially outward direction, therefore can determine the entrance and exit position of path.In other words, path entrance can be positioned at the inside (or adjoining position place) of madial wall and one of them sidewall of outer side wall.
Please note, although the utility model is mainly described with reference to the first order of exemplary land gas turbine engine, but the utility model goes for any turbine stage, and the those of ordinary skill in affiliated field also will be recognized, embodiment of the present utility model can also be used in other turbo machines, comprise turbo machine used in aircraft, or in the engine with revolving cylinders of other types.
Although the utility model has combined and has been considered to most practicability at present and most preferred embodiment is described, but should be appreciated that, the utility model is not limited to the disclosed embodiments, and is intended to contain the various amendment in the spirit and scope of following claims and equivalent.
Claims (20)
1. a turbomachine injection nozzle wheel blade section, described turbomachine injection nozzle wheel blade section comprises:
One or more nozzle wheel blade, described nozzle wheel blade extends between radially inner side wall and radial outside wall, and each nozzle wheel blade has peripheral edge wall, and described peripheral edge wall comprises leading edge and trailing edge; And the coolant path of at least one radial directed, described coolant path is formed in described peripheral edge wall, has the entrance being positioned at described madial wall and described one of them side-walls of outer side wall.
2. turbomachine injection nozzle wheel blade section according to claim 1, the coolant path of at least one radial directed wherein said comprises the coolant path of multiple radial directed, and the coolant path of described multiple radial directed comprises a coolant path of the forefront being positioned at described leading edge.
3. turbomachine injection nozzle wheel blade section according to claim 1, wherein said nozzle wheel blade hollow substantially, and wherein the rib of radial directed is provided on the internal surface of described peripheral edge wall, adjoins the coolant path of at least one radial directed described and extend along it.
4. turbomachine injection nozzle wheel blade section according to claim 2, wherein said nozzle wheel blade hollow, and wherein the rib of radial directed is provided on the internal surface of described peripheral edge wall, adjoins each coolant path in the coolant path of described multiple radial directed and extend along it.
5. turbomachine injection nozzle wheel blade section according to claim 4, the rib of wherein said radial directed is arranged in the internal cooling cavity of described nozzle wheel blade.
6. turbomachine injection nozzle wheel blade section according to claim 1, the coolant path of at least one radial directed wherein said comprises multiple coolant path, the spaced position place of described multiple coolant path between described frontier and rear around described peripheral edge wall, and wherein the rib of radial directed is provided on the internal surface of described peripheral edge wall, adjoins each coolant path in described multiple coolant path and extend along it.
7. turbomachine injection nozzle wheel blade section according to claim 2, the coolant path of wherein said multiple radial directed has outlet, and the Different Diameter between described madial wall and outer side wall is to position.
8. turbomachine injection nozzle wheel blade section according to claim 1, wherein each described wheel blade comprises internal cooling loop, the coolant path of described internal cooling circuit and at least one radial directed described is independent and be not connected, and the outlet of at least one path described is arranged in another sidewall of described madial wall and outer side wall.
9. turbomachine injection nozzle wheel blade section according to claim 1, the coolant path of at least one radial directed wherein said has circle, rectangle or race track shaped cross-section shape.
10. turbomachine injection nozzle wheel blade section according to claim 1, wherein the coolant path of at least one radial directed radially length dimension there is the part of multiple different-diameter.
11. 1 kinds of turbogenerators, described turbogenerator comprises compressor, at least one burner and at least one turbine stage, described turbine stage comprises a line fixed nozzle wheel blade, described fixed nozzle wheel blade extends between radially inner side wall and radial outside wall, each nozzle wheel blade has peripheral edge wall, and described peripheral edge wall comprises leading edge and trailing edge; And the coolant path of at least one radial directed, described coolant path is formed in described peripheral edge wall, has the entrance being positioned at described madial wall and described one of them side-walls of outer side wall.
12. turbogenerators according to claim 10, the coolant path of at least one radial directed wherein said comprises the coolant path of multiple radial directed, and the coolant path of described multiple radial directed comprises a coolant path of the forefront being positioned at described leading edge.
13. turbogenerators according to claim 11, wherein said nozzle wheel blade hollow, and wherein the rib of radial directed is provided on the internal surface of described peripheral edge wall, adjoins the coolant path of at least one radial directed described and extends along it.
14. turbogenerators according to claim 12, wherein said nozzle wheel blade hollow, and wherein the rib of radial directed is provided on the internal surface of described peripheral edge wall, adjoins each coolant path in the coolant path of described multiple cardinal principle radial directed and extend along it.
15. turbogenerators according to claim 11, the rib of wherein said radial directed is arranged in the internal cooling cavity of described nozzle wheel blade.
16. turbogenerators according to claim 11, the coolant path of at least one radial directed wherein said comprises multiple coolant path, the spaced position place of described multiple coolant path between described frontier and rear around described peripheral edge wall, and wherein the rib of radial directed is provided on the internal surface of described peripheral edge wall, adjoins each coolant path in described multiple coolant path and extend along it.
17. turbogenerators according to claim 15, the coolant path of at least one radial directed wherein said has the outlet being connected to described internal cooling cavity.
18. turbogenerators according to claim 11, wherein said wheel blade comprises internal cooling loop, the coolant path of described internal cooling circuit and at least one radial directed described is independent and be not connected, and the outlet of at least one path described is arranged in another sidewall of described madial wall and outer side wall.
19. turbogenerators according to claim 11, the coolant path of at least one radial directed wherein said has circle, rectangle or race track shaped cross-section shape.
20. 1 kinds of turbogenerators, described turbogenerator comprises compressor, at least one burner and at least one turbine stage, described turbine stage comprises: a line fixed nozzle wheel blade, described fixed nozzle wheel blade extends between radially inner side wall and outer side wall, each nozzle wheel blade has peripheral edge wall, and described peripheral edge wall comprises leading edge and trailing edge; And the coolant path of multiple radial directed, described coolant path is included in described leading edge place, formed around described peripheral edge wall, the coolant path of described multiple cardinal principle radial directed extends along the radial length between described madial wall and outer side wall at least partly, and have entrance, described entrance is positioned at inside or the adjoining position place of described madial wall and described one of them sidewall of outer side wall; And strengthening rib, each cooling channel place of described strengthening rib in the coolant path of contiguous described multiple radial directed extends along the internal surface of described peripheral edge.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US14/048778 | 2013-10-08 | ||
| US14/048,778 US20150096306A1 (en) | 2013-10-08 | 2013-10-08 | Gas turbine airfoil with cooling enhancement |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204312137U true CN204312137U (en) | 2015-05-06 |
Family
ID=52693376
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420578804.5U Expired - Fee Related CN204312137U (en) | 2013-10-08 | 2014-10-08 | Turbogenerator and turbomachine injection nozzle wheel blade section |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20150096306A1 (en) |
| JP (1) | JP2015075103A (en) |
| CN (1) | CN204312137U (en) |
| CH (1) | CH708705A2 (en) |
| DE (1) | DE102014114244A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111927561A (en) * | 2020-07-31 | 2020-11-13 | 中国航发贵阳发动机设计研究所 | Rotary pressurizing structure for cooling turbine blade |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB201506728D0 (en) * | 2015-04-21 | 2015-06-03 | Rolls Royce Plc | Thermal shielding in a gas turbine |
| US20170002662A1 (en) * | 2015-07-01 | 2017-01-05 | United Technologies Corporation | Gas turbine engine airfoil with bi-axial skin core |
| FR3061512B1 (en) * | 2017-01-05 | 2020-10-23 | Safran Aircraft Engines | RADIAL ELEMENT OF TURBOMACHINE STATOR WITH A STRAIGHTENER |
| US10951095B2 (en) | 2018-08-01 | 2021-03-16 | General Electric Company | Electric machine arc path protection |
| FR3110197B1 (en) | 2020-05-14 | 2022-12-23 | Ge Energy Products France Snc | REACTIVE GAS FUEL PURGE SYSTEM |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2275975A5 (en) * | 1973-03-20 | 1976-01-16 | Snecma | Gas turbine blade with cooling passages - holes parallel to blade axis provide surface layer of cool air |
| US5484258A (en) * | 1994-03-01 | 1996-01-16 | General Electric Company | Turbine airfoil with convectively cooled double shell outer wall |
| WO1998037310A1 (en) * | 1997-02-20 | 1998-08-27 | Siemens Aktiengesellschaft | Turbine blade and its use in a gas turbine system |
| US6290459B1 (en) * | 1999-11-01 | 2001-09-18 | General Electric Company | Stationary flowpath components for gas turbine engines |
| US6997679B2 (en) * | 2003-12-12 | 2006-02-14 | General Electric Company | Airfoil cooling holes |
| JP4773457B2 (en) * | 2004-12-24 | 2011-09-14 | アルストム テクノロジー リミテッド | Components with embedded passages, especially hot gas components of turbomachines |
| US20110110772A1 (en) * | 2009-11-11 | 2011-05-12 | Arrell Douglas J | Turbine Engine Components with Near Surface Cooling Channels and Methods of Making the Same |
| US8770936B1 (en) * | 2010-11-22 | 2014-07-08 | Florida Turbine Technologies, Inc. | Turbine blade with near wall cooling channels |
-
2013
- 2013-10-08 US US14/048,778 patent/US20150096306A1/en not_active Abandoned
-
2014
- 2014-09-30 JP JP2014199551A patent/JP2015075103A/en active Pending
- 2014-09-30 DE DE201410114244 patent/DE102014114244A1/en not_active Withdrawn
- 2014-10-06 CH CH01525/14A patent/CH708705A2/en not_active Application Discontinuation
- 2014-10-08 CN CN201420578804.5U patent/CN204312137U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111927561A (en) * | 2020-07-31 | 2020-11-13 | 中国航发贵阳发动机设计研究所 | Rotary pressurizing structure for cooling turbine blade |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2015075103A (en) | 2015-04-20 |
| DE102014114244A1 (en) | 2015-04-09 |
| US20150096306A1 (en) | 2015-04-09 |
| CH708705A2 (en) | 2015-04-15 |
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