CN111335965B - Turbine rotor device with cooling and compressing structure - Google Patents
Turbine rotor device with cooling and compressing structure Download PDFInfo
- Publication number
- CN111335965B CN111335965B CN202010157757.7A CN202010157757A CN111335965B CN 111335965 B CN111335965 B CN 111335965B CN 202010157757 A CN202010157757 A CN 202010157757A CN 111335965 B CN111335965 B CN 111335965B
- Authority
- CN
- China
- Prior art keywords
- tenon
- cooling
- mortise
- groove
- turbine rotor
- 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.)
- Active
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
-
- 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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/32—Locking, e.g. by final locking blades or keys
- F01D5/326—Locking of axial insertion type blades by other means
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a turbine rotor device with a cooling and compressing structure, which comprises a blade and a wheel disc which are connected by a fir-shaped tenon and a mortise in a matching way, and further comprises a cooling and compressing device which is arranged in a gap between the end surface of the tenon and the bottom of the mortise in an interference way, wherein the cooling and compressing device is provided with a lower main supporting column and a branch supporting column which is symmetrically arranged at the upper part, the main supporting column and the branch supporting column respectively form a plurality of cold air channels with the end surface of a tenon and the mortise, so that the tenon and the mortise are fixed in relative positions, the effective cold air convection area is increased, the cold air channel space and the effective convection area are increased, the temperature of a wheel rim part and the connecting part of the blade tenon and the wheel disc mortise are reduced, the thermal stress of the blade tenon and the wheel disc mortise is reduced, and the creep life of the blade tenon and the wheel disc mortise structure and.
Description
Technical Field
The invention relates to the technical field of aircraft engines, in particular to a turbine rotor device with a cooling and compressing structure.
Background
Aeroengine turbine rotor adopts fir type tenon and tongue-and-groove connection structure to realize the assembly of turbine disc and blade usually, this structure is the important link of aeroengine structure, the intensity of rotor part is directly related to its structural design's rationality, life-span and reliability, and greatly influence the mass-pushed ratio of engine, at present, fir type tenon and tongue-and-groove connection structure that aeroengine turbine rotor adopted, the centrifugal force that high-speed pivoted blade produced makes the blade tenon, the temperature that rim plate tongue-and-groove connection position produced reaches and even exceeds 900K, and produce higher thermal stress, simultaneously the blade tenon, the life of turbine rotor also can greatly reduced to the fretting friction between rim plate tongue-and-groove connection position. With the continuous improvement of performance requirements of aero-engines, the working environment of turbine components is more severe, the defects of short service life and low reliability in the traditional fir-tree type disc-tenon connecting structure are more obvious, and the high-quality use requirements cannot be met.
Disclosure of Invention
The invention aims to overcome the defects and provides a turbine rotor device with a cooling and compressing structure, which enables the relative positions of a blade and a wheel disc which are connected by matching a fir-shaped tenon and a mortise to be stable in a non-working state and a working state, increases the cold air passage space of a connecting part, increases the effective convection area, reduces the temperature of a wheel rim part and the connecting part of the blade tenon and the wheel disc mortise, reduces the thermal stress of the blade tenon, and improves the creep life of the blade tenon, the wheel disc mortise structure and the wheel disc wheel rim.
The specific technical scheme provided by the invention is as follows:
the utility model provides a turbine rotor device who contains cooling compact structure, includes blade and rim plate through fir type tenon and tongue-and-groove accordant connection, still includes the interference install at the tenon terminal surface with the cooling closing device in tongue-and-groove bottom clearance, cooling closing device is equipped with the main tributary dagger and is located the branch support column that main tributary dagger upper end symmetry set up, the main tributary dagger the branch support column respectively with the tenon tooth terminal surface reaches the tongue-and-groove forms a plurality of air conditioning passageways, makes the tenon tooth with tongue-and-groove relative position is fixed, and the effective convection area increase of air conditioning.
It should be noted that, the cooling and compressing device applies an upward pressure to the tenon of the blade in the non-working state, so that the tenon and the mortise are in a pressing and fitting state, and the relative sliding in the non-working state is reduced, and the cooling and compressing device can provide pressure to the tenon in the working state, so that the sliding friction force between the tenon and the mortise is increased, the relative sliding between the tenon of the blade and the mortise of the wheel disc is greatly reduced, the cooling space is increased, and meanwhile, a gap is reserved between the tenon of the blade and the mortise of the wheel disc to ensure that the tenon can freely expand after being connected so as to reduce the thermal stress generated on the tenon, and simultaneously, the creep life of the tenon of the blade, the mortise structure of the wheel disc and the wheel disc rim is prolonged, and the service life of the turbine rotor device and even the whole engine is prolonged.
Preferably, cooling closing device is "Y" form, the lower terminal surface of main tributary support post with the tongue-and-groove bottom is laminated, the left branch support post symmetry set up the up end of left branch support post and right branch support post all with the tenon tooth terminal surface is laminated mutually, the lateral surface of left branch support post and right branch support post all with the tongue-and-groove wall is laminated mutually.
Preferably, the upper end surfaces of the left supporting column and the right supporting column are planes and are matched with the tenon tooth end surfaces.
Preferably, the lower end face of the main supporting column is an arc face and is matched with the bottom face of the mortise.
Preferably, the left support column and the right support column form an upper groove, and the upper groove and the tenon tooth end face form an upper cooling channel.
Preferably, the main supporting column, the left supporting column and the right supporting column respectively form a left cooling channel and a right cooling channel which are symmetrically arranged.
Preferably, the cross-sectional area of the upper cooling gallery in the plane of the dovetail is approximately 1/4 the cross-sectional area of the side cooling air gallery.
Preferably, the tenon is equipped with first tenon tooth and second tenon tooth, the tongue-and-groove corresponds the setting and is the first tongue-and-groove and the second tongue-and-groove of surrounding form, the upside shoulder of first tenon tooth with the upside wall in first tongue-and-groove is laminated mutually, the upside shoulder of second tenon tooth with the upside wall in second tongue-and-groove is laminated mutually.
Preferably, the tenon end face of the first tenon tooth and the upper side shoulder are in arc transition, so that the arc face of the first tenon tooth, the first mortise, the left support column and the upper end face of the right support column form a left space and a right space which are symmetrically arranged.
Preferably, the connection between the first tenon tooth and the side face of the second tenon tooth is arc transition, and the corresponding connection between the side faces of the first tenon groove and the second tenon groove is arc transition.
It should be noted that, the cooling and compressing device applies an upward pressure to the tenon of the blade in the non-working state, so that the tenon and the mortise are in a pressing and fitting state, the relative sliding of the contact surface of the tenon and the mortise in the non-working state is reduced, the cooling and compressing device can provide pressure for the tenon in the working state, so that the sliding friction force between the tenon and the mortise is increased, the relative sliding between the tenon of the blade and the mortise of the wheel disc is greatly reduced, the cooling space is increased, and meanwhile, a gap is reserved between the tenon of the blade and the mortise of the wheel disc to ensure that the tenon can freely expand after being connected so as to reduce the thermal stress generated on the tenon.
It should be noted that, through being "Y" form cooling closing device's setting makes the tip of first tenon tooth first tongue-and-groove with form left space, right space, go up cooling channel, left side cooling channel and right side cooling channel between the cooling closing device respectively, a plurality of air conditioning channels of scientific distribution, but the flow area and the circulation speed of greatly increased air conditioning have increaseed convection efficiency effectively, have greatly reduced the temperature of blade tenon and rim plate tongue-and-groove structure and rim plate rim, have reduced the thermal stress of blade tenon, have improved the creep life-span of blade tenon and rim plate tongue-and-groove structure and rim plate rim simultaneously, have improved turbine rotor device is even the life-span of whole engine.
The invention has the beneficial effects that:
adopt this turbine rotor device who contains cooling compact structure, the device makes blade and rim plate through fir type tenon and tongue-and-groove cooperation connection relatively position stable under non-operating condition and operating condition, relative slip has been reduced, the cold wind passageway space of connection position has been increased simultaneously, effective convection area has been increased, the temperature at rim part and blade tenon and rim plate tongue-and-groove connection position has been reduced, leave the clearance between blade tenon and the rim plate tongue-and-groove simultaneously and can freely expand in order to reduce the thermal stress that produces on the tenon after guaranteeing the tenon connection, the creep life-span of blade tenon and rim plate tongue-and-groove structure and rim plate has been improved, improved turbine rotor device has even the life-span of whole engine.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the application and together with the description serve to explain the application and not to limit the application. In the drawings:
FIG. 1 is a schematic view of a blade and disk connection of the present invention;
FIG. 2 is an enlarged view of N of FIG. 1;
FIG. 3 is a schematic view of a tenon construction;
FIG. 4 is a schematic view of a tongue and groove configuration;
fig. 5 is a schematic view of the cooling and compressing device.
Wherein: 100-blade; 110-tenon; 113-tenon tooth end face;
111 — a second cog; 111-1 — second upper tooth surface; 112-a first cog; 112-1 — first upper tooth surface;
200-a wheel disc; 210-tongue and groove;
211 — a second tongue and groove; 211-1 — second upper sidewall;
212 — a first tongue and groove; 212-1 — first upper sidewall; 212-2-tongue and groove floor;
300-cooling the compacting device; 310-branch supporting column; 310-1-left upper end face, right upper end face; 310-2-left support column; 320-main supporting column; a right support column; 320-1 — main support end face;
a-upper cooling channel; b, a left cooling channel and a right cooling channel; c — first left space, first right space; d-second left space, second right space.
Detailed Description
As used in the specification and in the claims, certain terms are used to refer to particular components. As one skilled in the art will appreciate, manufacturers may refer to a component by different names. This specification and claims do not intend to distinguish between components that differ in name but not function. In the following description and in the claims, the terms "include" and "comprise" are used in an open-ended fashion, and thus should be interpreted to mean "include, but not limited to. The terms "first", "second", and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implying any number of technical features indicated; "plurality" means equal to or greater than three; the description which follows is a preferred embodiment of the present application, but is made for the purpose of illustrating the general principles of the application and not for the purpose of limiting the scope of the application. The protection scope of the present application shall be subject to the definitions of the appended claims.
Referring to fig. 1 to 5, in an embodiment of the present invention, a turbine rotor device including a cooling and compressing structure includes a blade 100 and a disk 200 that are connected to each other by a fir-tree-shaped tenon 110 and a mortise 210 in a matching manner, and further includes a cooling and compressing device 300 that is installed in a gap between a tenon end face and a bottom of the mortise in an interference manner, where the cooling and compressing device 300 is provided with a main supporting pillar 320 and a sub supporting pillar 310 that are symmetrically disposed at an upper end of the main supporting pillar, and the main supporting pillar 320 and the sub supporting pillar 310 respectively form a plurality of cooling air channels with the tenon end face 113 and the mortise 210, so that the positions of the tenon and the mortise are fixed relative to each other, and an effective cooling air convection area is increased.
It should be noted that, the cooling and compressing device applies an upward pressure to the tenon of the blade in the non-working state, so that the tenon and the mortise are in a pressing and fitting state, and the relative sliding in the non-working state is reduced, and the cooling and compressing device can provide pressure to the tenon in the working state, so that the sliding friction force between the tenon and the mortise is increased, the relative sliding between the tenon of the blade and the mortise of the wheel disc is greatly reduced, the cooling space is increased, and meanwhile, a gap is reserved between the tenon of the blade and the mortise of the wheel disc to ensure that the tenon can freely expand after being connected so as to reduce the thermal stress generated on the tenon, and simultaneously, the creep life of the tenon of the blade, the mortise structure of the wheel disc and the wheel disc rim is prolonged, and the service life of the turbine rotor device and even the whole engine is prolonged.
Preferably, the cooling and pressing device 300 is "Y" shaped, the main supporting end face 320-1 of the main supporting column 320 is attached to the bottom face 212-2 of the mortise 210, the left upper end face 310-1 of the left supporting column 310-2 and the right upper end face 310-1 of the right supporting column 310-2, which are symmetrically arranged with respect to the sub supporting column 310, are both attached to the tenon tooth end face 113, and the outer side faces of the left supporting column 310-2 and the right supporting column 310-2 are both attached to the mortise wall.
Preferably, the left upper end surface 310-1 of the left support column 310-2 and the right upper end surface 310-1 of the right support column 310-2 are both flat surfaces, and are matched with the tenon tooth end surface 113.
Preferably, the main supporting end surface 320-1 of the lower part of the main supporting pillar 320 is a cambered surface, and matches with the mortise bottom surface 212-2.
Preferably, the left support column 310-2 and the right support column 310-2 form an upper groove, and the upper groove and the tenon tooth end surface 113 form an upper cooling channel A.
Preferably, the main supporting column 320 and the left supporting column 310-2 and the right supporting column 310-2 and the wall of the first mortise 212 form a left cooling channel B and a right cooling channel B, respectively, which are symmetrically arranged.
Preferably, the cross-sectional area of the upper cooling gallery A in the plane of the dovetail is approximately 1/4 times the cross-sectional area of the left or right cooling gallery B.
Preferably, the tenon 110 is provided with a first tenon tooth 112 and a second tenon tooth 111, the tenon groove 210 is correspondingly provided with a first tenon groove 212 and a second tenon groove 211 which are in a surrounding shape, a first upper tooth surface 112-1 of the first tenon tooth 112 is attached to a first upper side wall 212-1 of the first tenon groove 212, and a second upper tooth surface 111-1 of the second tenon tooth 111 is attached to a second upper side wall 211-1 of the second tenon groove 211.
Preferably, the tenon tooth end surface 113 of the first tenon tooth 112 and the first upper tooth surface 112-1 are in circular arc transition, so that the circular arc surface of the first tenon tooth 112, the first mortise 212, the left upper end surface 310-1 of the left support pillar 310-2 and the right upper end surface 310-1 of the right support pillar 310-2 form a first left space C and a first right space C which are symmetrically arranged.
Preferably, the connection between the first tenon tooth 112 and the side of the second tenon tooth 111 is an arc transition, and the connection between the corresponding first tenon slot 212 and the side of the second tenon slot 211 is an arc transition.
It should be noted that, in the non-operating state, the cooling and pressing device 300 applies an upward pressure to the tenon 110 of the blade 100, the tenon 110 and the mortise 210 are in a pressing fit state, the relative slippage of the contact surface of the tenon 110 and the mortise 210 in a non-working state is reduced, the cooling and compressing device 300 can provide pressure for the tenon 110 under the working state, so that the sliding friction force between the tenon 110 and the mortise 210 is increased, the relative sliding between the tenon 110 of the blade and the mortise 210 of the wheel disc 200 is greatly reduced, the cooling space is increased, meanwhile, a gap is reserved between the blade tenon and the wheel disc mortise to ensure that the tenon can expand freely after being connected so as to reduce the thermal stress generated on the tenon tooth, meanwhile, the creep life of the blade tenon, the wheel disc mortise structure and the wheel disc rim is prolonged, and the service life of the turbine rotor device and even the service life of the whole engine are prolonged.
It should be noted that the main supporting end surface 320-1 and the mortise bottom surface 212-2, which are mutually matched, may also be provided with a plane or other contact surface; the left upper end surface 310-1, the right upper end surface 310-1 and the tenon tooth end surface 113 which are matched with each other can also be provided with cambered surfaces or contact surfaces in other forms; contact surfaces fulfilling the function of the invention are within the scope of the invention.
It should be noted that, by the arrangement of the cooling and compressing device 300 in the shape of "Y", a first left space C, a first right space C, an upper cooling channel a, a left cooling channel B, and a right cooling channel B are respectively formed between the tenon tooth end surface 113 of the first tenon tooth 112, the first tenon groove 212, and the cooling and compressing device 300, and in addition, a second left space D and a second right space D formed by the second tenon tooth 111 and the second tenon groove 211, a plurality of cooling air channels are scientifically distributed, can greatly increase the flow area and the flow speed of cold air, effectively increase the convection efficiency, greatly reduce the temperature of the blade tenon, the wheel disc mortise structure and the wheel disc rim, reduce the thermal stress of the blade tenon, meanwhile, the creep life of the blade tenon, the wheel disc mortise structure and the wheel disc rim is prolonged, and the service life of the turbine rotor device and even the service life of the whole engine are prolonged.
The invention has the beneficial effects that:
by adopting the turbine rotor device with the cooling and compressing structure, the device ensures that the blade and the wheel disc which are connected by matching the fir-shaped tenon and the mortise are relatively stable in position under the non-working state and the working state, reduces the relative sliding, increases the cold air channel space of the connecting part, increases the effective convection area, reduces the temperature of the wheel rim part and the connecting part of the blade tenon and the wheel disc mortise, and simultaneously leaves a gap between the blade tenon and the wheel disc mortise to ensure that the tenon can freely expand after being connected so as to reduce the thermal stress generated on the tenon, reduce the thermal stress of the blade tenon, improve the creep life of the blade tenon, the wheel disc mortise structure and the wheel disc wheel rim, and improve the service life of the turbine rotor device and even the whole engine.
The foregoing description shows and describes several preferred embodiments of the present application, but as aforementioned, it is to be understood that the application is not limited to the forms disclosed herein, but is not to be construed as excluding other embodiments and is capable of use in various other combinations, modifications, and environments and is capable of changes within the scope of the application as described herein, commensurate with the above teachings, or the skill or knowledge of the relevant art. And that modifications and variations may be effected by those skilled in the art without departing from the spirit and scope of the application, which is to be protected by the claims appended hereto.
Claims (9)
1. The utility model provides a turbine rotor device who contains cooling compact structure, includes blade and rim plate through fir type tenon and tongue-and-groove accordant connection, its characterized in that: still include the interference install at the tenon terminal surface with the cooling closing device of "Y" form in tongue-and-groove bottom clearance, cooling closing device is equipped with the main tributary dagger and is located the branch support column that main tributary dagger upper end symmetry set up, the main tributary dagger divide the support column to reach with the tenon tooth terminal surface respectively the tongue-and-groove shape matches and compresses tightly the laminating, forms cooling channel and a plurality of side air conditioning passageway, the cross sectional area of going up cooling channel in the tenon plane occupies about side air conditioning passageway cross sectional area's 1/4, makes the tenon tooth with tongue-and-groove relative position is fixed, and the effective convection area of air conditioning increases.
2. The turbine rotor device with the cooling and compressing structure as claimed in claim 1, wherein the lower end face of the main supporting column is attached to the bottom of the mortise, the upper end faces of the left and right supporting columns symmetrically arranged on the main supporting column are attached to the end face of the tenon, and the outer side faces of the left and right supporting columns are attached to the mortise.
3. The turbine rotor device with the cooling and compacting structure as claimed in claim 2, wherein the upper end surfaces of the left supporting column and the right supporting column are flat surfaces and are matched with the tenon tooth end surfaces.
4. The turbine rotor assembly with cooling and compacting structure of claim 3, wherein the lower end surface of the main support pillar is a cambered surface matching the bottom surface of the mortise.
5. The turbine rotor assembly including the cooling packing structure of claim 4, wherein the left support post and the right support post form an upper groove, the upper groove and the tenon tooth end face forming an upper cooling channel.
6. The turbine rotor apparatus including a cooling packing structure according to claim 5, wherein the main support column and the left and right support columns form a left cooling channel and a right cooling channel, respectively, which are symmetrically disposed.
7. The turbine rotor device with the cooling and compressing structure as claimed in claim 6, wherein the tenon is provided with a first tenon tooth and a second tenon tooth, the tenon groove is correspondingly provided with a first tenon groove and a second tenon groove which are arranged in an enclosing manner, an upper side shoulder of the first tenon tooth is attached to an upper side wall of the first tenon groove, and an upper side shoulder of the second tenon tooth is attached to an upper side wall of the second tenon groove.
8. The turbine rotor device with the cooling and compressing structure as claimed in claim 7, wherein the tenon end surface of the first tenon tooth and the upper side shoulder are in arc transition, so that the arc surface of the first tenon tooth, the first mortise and the upper end surfaces of the left support column and the right support column form a left space and a right space which are symmetrically arranged.
9. The cooling-compaction-structure-containing turbine rotor device of claim 8, wherein the connections between the first tenon tooth and the second tenon tooth side are all circular-arc transitions, and the corresponding connections between the first tenon slot and the second tenon slot side are all circular-arc transitions.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010157757.7A CN111335965B (en) | 2020-03-09 | 2020-03-09 | Turbine rotor device with cooling and compressing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010157757.7A CN111335965B (en) | 2020-03-09 | 2020-03-09 | Turbine rotor device with cooling and compressing structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111335965A CN111335965A (en) | 2020-06-26 |
| CN111335965B true CN111335965B (en) | 2021-01-05 |
Family
ID=71179878
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010157757.7A Active CN111335965B (en) | 2020-03-09 | 2020-03-09 | Turbine rotor device with cooling and compressing structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111335965B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117307254B (en) * | 2023-11-28 | 2024-01-23 | 成都中科翼能科技有限公司 | Turbine rotor structure of gas turbine |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB944327A (en) * | 1959-06-12 | 1963-12-11 | Ass Elect Ind | Locking means for turbine or compressor blading |
| US5540552A (en) * | 1994-02-10 | 1996-07-30 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Turbine engine rotor having axial or inclined, issuing blade grooves |
| JP2003314369A (en) * | 2002-04-26 | 2003-11-06 | Ishikawajima Harima Heavy Ind Co Ltd | Dovetail shim |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001012205A (en) * | 1999-06-29 | 2001-01-16 | Mitsubishi Heavy Ind Ltd | Gas turbine moving blade cooling flow rate adjusting device |
| JP2005273646A (en) * | 2004-02-25 | 2005-10-06 | Mitsubishi Heavy Ind Ltd | Moving blade element and rotary machine having the moving blade element |
| US8206116B2 (en) * | 2005-07-14 | 2012-06-26 | United Technologies Corporation | Method for loading and locking tangential rotor blades and blade design |
| US10094228B2 (en) * | 2015-05-01 | 2018-10-09 | General Electric Company | Turbine dovetail slot heat shield |
| DE102015111746A1 (en) * | 2015-07-20 | 2017-01-26 | Rolls-Royce Deutschland Ltd & Co Kg | Cooled turbine wheel, in particular for an aircraft engine |
-
2020
- 2020-03-09 CN CN202010157757.7A patent/CN111335965B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB944327A (en) * | 1959-06-12 | 1963-12-11 | Ass Elect Ind | Locking means for turbine or compressor blading |
| US5540552A (en) * | 1994-02-10 | 1996-07-30 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Turbine engine rotor having axial or inclined, issuing blade grooves |
| JP2003314369A (en) * | 2002-04-26 | 2003-11-06 | Ishikawajima Harima Heavy Ind Co Ltd | Dovetail shim |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111335965A (en) | 2020-06-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8052389B2 (en) | Internally cooled airfoils with load carrying members | |
| EP2108785B1 (en) | Turbine blade and vane assembly with a ceramic platform | |
| KR101366908B1 (en) | Split ring cooling structure and gas turbine | |
| US2452782A (en) | Construction of rotors for compressors and like machines | |
| CN111335965B (en) | Turbine rotor device with cooling and compressing structure | |
| CN1629449B (en) | Turbine blade frequency tuned pin bank | |
| JP5503140B2 (en) | Divergent turbine nozzle | |
| US20070253815A1 (en) | Cooled gas turbine aerofoil | |
| US2613058A (en) | Cooled bladed rotor | |
| CN111271132B (en) | Turbine rotor device with cooling and compressing structure | |
| JPS6146644B2 (en) | ||
| CN103119247A (en) | Gas turbine blade | |
| CN104364581A (en) | Gas turbine engine wall | |
| US8113784B2 (en) | Coolable airfoil attachment section | |
| CN103184890A (en) | Composite blade assembly | |
| CN110145372B (en) | Steam turbine rotor forked blade mounting structure and mounting method thereof | |
| CN104196572A (en) | Twin-web rotor disc provided with disc cavity flow-guide rib plates | |
| CN103206270A (en) | Method for cooling turbine disc and moving blade of combustion gas turbine | |
| CN107060889A (en) | A kind of double disc turbine disks with disk chamber turbulence columns | |
| EP2719863B1 (en) | Turbine blade | |
| CN102400717A (en) | Turbine blade platform cooling systems | |
| CN108374692B (en) | Turbine wheel disc and turbine engine | |
| CN111305908B (en) | Turbine rotor device with compression structure | |
| CN106761945A (en) | A kind of low inertia turbine disc structure | |
| CN205532724U (en) | Turbine disc, turbine rotor that has this turbine disc and gas turbine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |