CN115142906B - Connecting structure for rear end of inner wall of combustor flame tube and root of blade of turbine guider - Google Patents
Connecting structure for rear end of inner wall of combustor flame tube and root of blade of turbine guider Download PDFInfo
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- CN115142906B CN115142906B CN202211071378.1A CN202211071378A CN115142906B CN 115142906 B CN115142906 B CN 115142906B CN 202211071378 A CN202211071378 A CN 202211071378A CN 115142906 B CN115142906 B CN 115142906B
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- Prior art keywords
- turbine
- wall
- rear end
- sealing ring
- combustor
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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
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
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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
- F01D9/02—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
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/60—Support structures; Attaching or mounting means
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The application belongs to the technical field of non-varactor formula engine design, concretely relates to combustor liner inner wall rear end and turbine director blade root connection structure, include: a combustor basket; a turbine vane, wherein the root of each blade has a first locating hole; the axial sealing ring is provided with a plurality of second positioning holes; each positioning pin is correspondingly inserted into one first positioning hole and one second positioning hole; the baffle ring is connected to the inner ring of the turbine guider and presses each positioning pin towards the direction of the turbine guider; and each spring is correspondingly sleeved on one positioning pin, and the axial sealing ring is attached to the rear end of the inner wall of the flame tube of the combustion chamber by means of the elastic force of the spring.
Description
Technical Field
The application belongs to the technical field of non-variable-volume engine design, and particularly relates to a connecting structure for the rear end of the inner wall of a flame tube of a combustion chamber and the root of a blade of a turbine guide vane.
Background
The turbine sets up at the combustor rear portion among the aeroengine, and the mode of axial grafting is connected between combustor flame tube inner wall rear end and turbine director blade root, as shown in figure 1, this kind of technical scheme has following defect:
when the engine works, the combustor flame tube and the turbine guider work at different temperatures and can be out of shape in an inconsistent mode, the axial splicing part between the rear end of the inner wall of the combustor flame tube and the root part of the blade of the turbine guider bears large stress, abrasion easily occurs, sealing failure is caused, air flow leakage occurs, and the overall performance of the engine is affected.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present application.
Disclosure of Invention
The object of the present application is to provide a combustor basket inner wall aft end and turbine vane root attachment arrangement that overcomes or alleviates at least one of the known disadvantages of the prior art.
The technical scheme of the application is as follows:
a combustor basket inner wall rear end and turbine vane root connection structure comprising:
a combustor basket;
a turbine vane, wherein the root of each blade has a first locating hole;
the axial sealing ring is provided with a plurality of second positioning holes;
each positioning pin is correspondingly inserted into one first positioning hole and one second positioning hole;
the baffle ring is connected to the inner ring of the turbine guider and presses each positioning pin towards the direction of the turbine guider;
and each spring is correspondingly sleeved on one locating pin, and the axial sealing ring is attached to the rear end of the inner wall of the flame tube of the combustion chamber by means of the elastic force of the spring.
According to at least one embodiment of the application, in the connection structure of the rear end of the inner wall of the combustor basket and the root of the turbine guide vane, the outer edge of the axial sealing ring is bent towards the combustor basket and abuts against the rear end of the inner wall of the combustor basket.
According to at least one embodiment of the application, in the connection structure of the rear end of the inner wall of the combustor basket and the root of the turbine guide vane, the edge of the outer edge of the axial sealing ring tilts towards the direction of the turbine guide vane.
According to at least one embodiment of the present application, in the above-mentioned connection structure of the rear end of the inner wall of the combustor basket and the root of the turbine nozzle blade, the baffle ring is connected to the inner ring of the turbine nozzle through a plurality of bolt fasteners.
According to at least one embodiment of the present application, in the above-mentioned structure for connecting the rear end of the inner wall of the combustor basket and the root of the turbine vane, the structure further comprises:
the radial sealing ring is provided with a plurality of third positioning holes; each positioning pin is correspondingly inserted into one third positioning hole;
the outer edge of the radial sealing ring is bent towards the direction of the turbine guide device and is attached to the inner side of the lower edge plate of each blade of the turbine guide device.
According to at least one embodiment of the present application, in the above-mentioned structure for connecting the rear end of the inner wall of the combustor basket and the root of the turbine vane, the edge of the outer edge of the radial seal ring is tilted inward.
The application has at least the following beneficial technical effects:
the utility model provides a rear end of combustor flame tube inner wall and turbine director blade root connection structure, wherein design presses each locating pin with the fender ring that connects on the inner ring of turbine director, utilize the locating pin with the axial seal ring location in the root of each blade in the turbine director, and then with the spring of cup jointing on each locating pin make the axial seal ring paste on the rear end of combustor flame tube inner wall, realize the reliable seal between combustor flame tube inner wall rear end and turbine director blade root, when taking place uncoordinated deformation between combustor flame tube and turbine director, can the relative slip with combustor flame tube inner wall rear end of axial seal ring release radial stress, and can the axial deformation release axial stress of each spring, avoid the part to take place the damage.
Drawings
FIG. 1 is a schematic view of a prior art engine combustor liner aft end and turbine vane root attachment;
FIG. 2 is a schematic view of a connection structure of an aft end of a combustor basket and a root of a turbine vane of an engine provided by an embodiment of the present application;
wherein:
1-a combustor basket; 2-a turbine guide; 3-a blade; 4-axial sealing ring; 5-positioning pins; 6-baffle ring; 7-inner ring; 8-a spring; 9-radial sealing ring.
For a better understanding of the present embodiments, certain elements of the drawings may be omitted, enlarged or reduced, and do not represent actual product dimensions, and the drawings are for illustrative purposes only and are not to be construed as limiting the present patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, and other related parts may refer to general designs, and in case of conflict, the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that devices or elements must have specific orientations, be constructed and operated in specific orientations, and that when the absolute position of an object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The word "comprising" or "comprises", and the like, when used in this description, is intended to specify the presence of stated elements or items, but not the exclusion of other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
The present application is described in further detail below with reference to fig. 1-2.
A combustor basket inner wall rear end and turbine vane root connection structure comprising:
a combustor basket 1;
a turbine nozzle 2 in which the root of each blade 3 has a first locating hole;
an axial seal ring 4 having a plurality of second positioning holes formed therein;
each positioning pin 5 is correspondingly inserted into one first positioning hole and one second positioning hole;
the baffle ring 6 is connected to the inner ring 7 of the turbine guider 2 and presses each positioning pin 5 towards the direction of the turbine guider 2;
and each spring 8 is correspondingly sleeved on one positioning pin 5, and the axial sealing ring 4 is attached to the rear end of the inner wall of the combustor liner 1 by means of the elastic force of the spring 8.
For the connection structure between the rear end of the inner wall of the combustor basket and the root of the turbine vane disclosed in the above embodiment, it can be understood by those skilled in the art that it is designed to press each positioning pin 5 with the retaining ring 6 connected to the inner ring 7 of the turbine vane 2, and to position the axial sealing ring 4 at the root of each vane 3 in the turbine vane 2 by using the positioning pin 5, and further to make the axial sealing ring 4 abut against the rear end of the inner wall of the combustor basket 1 by using the spring 8 sleeved on each positioning pin 5, so as to achieve reliable sealing between the rear end of the inner wall of the combustor basket 1 and the root of the vane 3 of the turbine vane 2, and when the uncoordinated deformation occurs between the combustor basket 1 and the turbine vane 2, the radial stress can be released by the sliding of the axial sealing ring 4 relative to the rear end of the inner wall of the combustor basket 1, and the axial stress can be released by the axial deformation of each spring 8, thereby avoiding the damage of the components.
In some optional embodiments, in the above-mentioned structure for connecting the rear end of the inner wall of the combustor basket and the root of the turbine vane 2, the outer edge of the axial sealing ring 4 is bent toward the combustor basket 1 and abuts against the rear end of the inner wall of the combustor basket 1, and has a certain radial and axial deformability, so that the sealing between the rear end of the inner wall of the combustor basket 1 and the root of the turbine vane 3 of the turbine vane 2 can be effectively ensured.
In some optional embodiments, in the above-mentioned structure for connecting the rear end of the inner wall of the combustor liner and the root of the turbine vane, the edge of the outer edge of the axial sealing ring 4 is tilted towards the direction of the turbine vane 2 and is far away from the rear end of the inner wall of the combustor liner 1, so as to avoid rubbing and damaging the rear end of the inner wall of the combustor liner 1.
In some alternative embodiments, in the above-mentioned structure for connecting the rear end of the inner wall of the combustor basket to the root of the turbine nozzle blade, the baffle ring 6 is connected to the inner ring 7 of the turbine nozzle 2 by a plurality of bolt fasteners.
In some optional embodiments, the above-mentioned structure for connecting the rear end of the inner wall of the combustor basket with the root of the turbine vane further comprises:
a radial seal ring 9 having a plurality of third positioning holes therein; each positioning pin 5 is correspondingly inserted into one third positioning hole;
the outer edge of the radial sealing ring 9 is bent towards the direction of the turbine guider 2 and is attached to the inner side of the lower edge plate of each blade 3 of the turbine guider 2 so as to form sealing at the position, and the rear end of the inner wall of the combustor liner 1 and the root of each blade 3 of the turbine guider 2 are reliably sealed in the radial direction and the axial direction by matching with the axial sealing ring 4.
In some optional embodiments, in the above-mentioned structure for connecting the rear end of the inner wall of the combustor liner and the blade root of the turbine vane, the edge of the outer edge of the radial sealing ring 9 is tilted inward, and is away from the inner side of the lower edge plate of each blade 3 of the turbine vane 2, so as to avoid scraping and rubbing damage to the inner side of the lower edge plate of each blade 3 of the turbine vane 2.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.
Claims (5)
1. The utility model provides a combustor flame tube inner wall rear end and turbine vane root connection structure which characterized in that includes:
a combustor basket (1);
a turbine nozzle (2) in which the root of each blade (3) has a first locating hole;
the axial sealing ring (4) is provided with a plurality of second positioning holes;
the positioning pins (5) are correspondingly inserted into the first positioning holes and the second positioning holes respectively;
the baffle ring (6) is connected to the inner ring (7) of the turbine guide device (2) and presses each positioning pin (5) towards the direction of the turbine guide device (2);
each spring (8) is correspondingly sleeved on one positioning pin (5), and the axial sealing ring (4) is attached to the rear end of the inner wall of the combustor liner (1) by means of the elastic force of the spring (8);
a radial sealing ring (9) provided with a plurality of third positioning holes; each positioning pin (5) is correspondingly inserted into one third positioning hole;
the outer edge of the radial sealing ring (9) is bent towards the turbine guide device (2) and is attached to the inner side of the lower edge plate of each blade (3) of the turbine guide device (2).
2. The combustor basket inner wall aft end and turbine vane root connection structure of claim 1,
the outer edge of the axial sealing ring (4) is bent towards the direction of the combustion chamber flame tube (1) and abuts against the rear end of the inner wall of the combustion chamber flame tube (1).
3. The combustor basket inner wall aft end and turbine nozzle blade root connection structure of claim 2,
the edge of the outer edge of the axial sealing ring (4) tilts towards the direction of the turbine guider (2).
4. The combustor basket inner wall aft end and turbine vane root connection structure of claim 1,
the baffle ring (6) is connected to the inner ring (7) of the turbine guide (2) through a plurality of bolt fasteners.
5. The combustor basket inner wall aft end and turbine vane root connection structure of claim 1,
the edge of the outer edge of the radial sealing ring (9) is tilted towards the inner side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211071378.1A CN115142906B (en) | 2022-09-02 | 2022-09-02 | Connecting structure for rear end of inner wall of combustor flame tube and root of blade of turbine guider |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211071378.1A CN115142906B (en) | 2022-09-02 | 2022-09-02 | Connecting structure for rear end of inner wall of combustor flame tube and root of blade of turbine guider |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115142906A CN115142906A (en) | 2022-10-04 |
| CN115142906B true CN115142906B (en) | 2022-11-22 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211071378.1A Active CN115142906B (en) | 2022-09-02 | 2022-09-02 | Connecting structure for rear end of inner wall of combustor flame tube and root of blade of turbine guider |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101551123A (en) * | 2008-04-03 | 2009-10-07 | 斯奈克玛动力部件公司 | Gas turbine combustion chamber having inner and outer walls subdivided into sectors |
| CN206647140U (en) * | 2017-04-07 | 2017-11-17 | 中国航发沈阳发动机研究所 | Turborotor bullet formula seal structure |
| CN110872985A (en) * | 2018-09-04 | 2020-03-10 | 通用电气公司 | Retaining ring for a turbine engine |
| CN111750380A (en) * | 2019-03-28 | 2020-10-09 | 中国航发湖南动力机械研究所 | Flame tube outlet connecting device |
| CN114837749A (en) * | 2021-02-02 | 2022-08-02 | 中国航发商用航空发动机有限责任公司 | Aircraft engine |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3372542A (en) * | 1966-11-25 | 1968-03-12 | United Aircraft Corp | Annular burner for a gas turbine |
| US20120183911A1 (en) * | 2011-01-18 | 2012-07-19 | General Electric Company | Combustor and a method for repairing a combustor |
-
2022
- 2022-09-02 CN CN202211071378.1A patent/CN115142906B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101551123A (en) * | 2008-04-03 | 2009-10-07 | 斯奈克玛动力部件公司 | Gas turbine combustion chamber having inner and outer walls subdivided into sectors |
| CN206647140U (en) * | 2017-04-07 | 2017-11-17 | 中国航发沈阳发动机研究所 | Turborotor bullet formula seal structure |
| CN110872985A (en) * | 2018-09-04 | 2020-03-10 | 通用电气公司 | Retaining ring for a turbine engine |
| CN111750380A (en) * | 2019-03-28 | 2020-10-09 | 中国航发湖南动力机械研究所 | Flame tube outlet connecting device |
| CN114837749A (en) * | 2021-02-02 | 2022-08-02 | 中国航发商用航空发动机有限责任公司 | Aircraft engine |
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| Publication number | Publication date |
|---|---|
| CN115142906A (en) | 2022-10-04 |
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