CN113280367B - Staged combustion chamber head with swirl pre-membrane plate structure - Google Patents
Staged combustion chamber head with swirl pre-membrane plate structure Download PDFInfo
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- CN113280367B CN113280367B CN202110606554.6A CN202110606554A CN113280367B CN 113280367 B CN113280367 B CN 113280367B CN 202110606554 A CN202110606554 A CN 202110606554A CN 113280367 B CN113280367 B CN 113280367B
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- swirl
- prefilming
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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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
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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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
Abstract
The present disclosure provides a staged combustion chamber head with swirl prefilming plate structure, comprising: the pre-combustion stage and the main combustion stage are sleeved outside the pre-combustion stage; the main combustion stage comprises an inner ring and a sleeve sleeved outside the inner ring; the inner ring is provided with a plurality of spray holes distributed along the circumferential direction; an annular air channel is formed between the inner ring and the sleeve; an axial rotational flow blade and a swirl prefilming plate are sequentially arranged in the air passage from front to back; the axial swirl blades are arranged in a plurality and are arranged along the circumferential direction; the swirling flow prefilming plate is annular and is formed by a plurality of segmental arcs arranged along the circumferential direction; the spray holes are arranged opposite to the arc ridges of the swirling flow prefilming plate, and two segmented arcs are arranged between any two adjacent spray holes; the radial heights of the front end and the rear end of the arc ridge are both larger than the radius of the outer surface of the inner ring and smaller than the radius of the inner surface of the sleeve.
Description
Technical Field
The disclosure relates to the technical field of aviation gas turbine combustors, in particular to a staged combustion chamber head with a swirl prefilming plate structure.
Background
With the gradual progress of the technology of the aero-engine, the engine combustion chamber adopts a more hierarchical combustion organization mode to achieve the purposes of high temperature rise or low emission. In the staged combustion, the pre-combustion stage mostly adopts a diffusion combustion mode, and the main combustion stage mostly adopts a premix combustion mode. The combustor of the type is applied to various related patents at home and abroad, such as U.S. patent application numbers 6363726, 6389815 and the like applied by the GE company in the United states, and patents 201210335832.X, 201310250022.9, 201410584846.4, 201810472110.6 and the like applied by the Beijing university of aerospace in China.
The main combustion stage oil quantity is mainly sprayed out from the main combustion stage, and then under the action of rotational flow air flow generated by the axial rotational flow blades, processes of fuel oil drop crushing, evaporation, oil-gas mixing and the like are generated, and mixed gas is formed in the combustion chamber for premixed combustion. Therefore, the main combustion stage fuel oil crushing and atomizing process is one of the key factors influencing the combustion performance and the emission system performance. The form of the main combustion stage direct injection matched with the pre-membrane plate is one of effective ways for improving the fuel atomization effect. The disclosed pre-film plate is mostly a cylindrical or conical pre-film plate, and has a structure shown in Chinese patent application No. 201610860748.8; or a blade pre-film plate, which has a structure shown in Chinese patent application No. 201810472110.6; all have certain effects of improving fuel atomization, but further research and improvement are still available.
Disclosure of Invention
To address at least one of the above technical problems, the present disclosure provides a staged combustion chamber head with a swirl prefilming plate structure.
According to one aspect of the present disclosure, a staged combustor head with a swirl prefilming plate structure includes: the pre-combustion stage and the main combustion stage are sleeved outside the pre-combustion stage;
the main combustion stage comprises an inner ring and a sleeve sleeved outside the inner ring;
the inner ring is provided with a plurality of spray holes distributed along the circumferential direction;
an annular air channel is formed between the inner ring and the sleeve;
the air passage is internally provided with an axial rotational flow blade and a swirl prefilming plate from front to back in sequence;
the axial swirl blades are arranged in a plurality and are arranged along the circumferential direction;
the swirling flow prefilming plate is annular and is formed by a plurality of segmental arcs arranged along the circumferential direction;
the spray holes are arranged opposite to the arc ridges of the swirling flow prefilming plate, and two segmented arcs are arranged between any two adjacent spray holes;
the radial heights of the front end and the rear end of the arc ridge are both larger than the radius of the outer surface of the inner ring and smaller than the radius of the inner surface of the sleeve.
According to at least one embodiment of the present disclosure, a leading end of the swirl prefilming plate is connected to a trailing end of the axial swirl vane.
According to at least one embodiment of the present disclosure, further comprising: a plurality of rib plates;
the inner side and the outer side of each rib plate are respectively connected to the swirl prefilming plate and the sleeve.
According to at least one embodiment of the present disclosure, the rib plate and the axial swirler vane are integrally formed.
According to at least one embodiment of the present disclosure, the inner side of the web is connected to the arc ridge of the swirl prefilming plate.
According to at least one embodiment of the present disclosure, two of the segmented arcs are located between any two adjacent rib plates.
According to at least one embodiment of the present disclosure, the diameters of the front and rear ends of the segmented arcs are unequal.
According to at least one embodiment of the present disclosure, the axial length of the swirl prefilming plate is 20% to 300% of the axial length of the axial swirl vanes.
According to at least one embodiment of the present disclosure, the thickness of the swirl prefilming plate is 20% to 100% of the thickness of the axial swirl vanes.
According to at least one embodiment of the present disclosure, the pre-combustion stage comprises: the device comprises a pre-combustion stage nozzle, a first-stage cyclone component and a second-stage cyclone component;
the pre-combustion stage nozzle is connected with the first-stage cyclone assembly;
the first-stage rotational flow component is connected with the second-stage rotational flow component;
the secondary swirler assembly is connected to the inner ring.
The invention has the beneficial effects that:
after the fuel is sprayed out of the spray holes, the fuel moves under the combined action of jet flow and air swirl, primary space atomization is formed in the air passage, and then the fuel just moves to the arc ridge of the swirl prefilming plate and is uniformly divided into two oil bundles by the arc ridge, the two oil bundles respectively form three-dimensional flow with swirl and swirl along the arc of the swirl prefilming plate, the fuel with large momentum returns to the center of the air passage along the arc to form secondary space atomization, the fuel with small momentum does not separate from the swirl prefilming plate, an oil film is formed on the swirl prefilming plate and moves to the rear end of the swirl prefilming plate, so that the oil film is broken and atomized, and the atomization quality is improved; compared with the prior art, the invention has the advantages that the fuel oil and the air form a comprehensive effect of rotational flow and swirl, the fuel oil spatial distribution is improved, the main combustion stage fuel oil atomization, evaporation and oil-gas mixing processes are further promoted, the premixing effect is improved, and the combustion performance and the emission performance of the combustion chamber are improved.
Drawings
The accompanying drawings, which are included to provide a further understanding of the disclosure and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the disclosure and together with the description serve to explain the principles of the disclosure.
FIG. 1 is a schematic view of a staged combustor head with a swirl prefilming plate structure according to an embodiment of the disclosure.
FIG. 2 is a schematic view of the staged combustion chamber head with the swirl prefilming plate structure shown in FIG. 1 cut in a plane through the central axis of the inner ring on the left side, and FIG. 2 is a schematic view of the staged combustion chamber head with the swirl prefilming plate structure shown in FIG. 1 cut in a plane at an angle to the central axis of the inner ring on the right side.
FIG. 3 is a schematic view of the geometric features of the swirl prefilmer plate in the staged combustor head with swirl prefilmer plate structure shown in FIG. 1.
FIG. 4 is a schematic view of the swirl prefilming plate and one of its fastening means in the staged combustion chamber head with swirl prefilming plate structure shown in FIG. 1.
FIG. 5 is a schematic view of the injection direction of the injection holes in the head of the staged combustion chamber with the swirl prefilming plate structure shown in FIG. 1.
FIG. 6 is a schematic diagram of the swirl effect of the swirl prefilming plate in the staged combustor head with swirl prefilming plate configuration shown in FIG. 1 compared to the swirl effect of a prior art prefilming plate, wherein the prior art prefilming plate is shown on the left side of FIG. 6, and the swirl prefilming plate configuration of the present disclosure is shown on the right side of FIG. 6.
FIG. 7 is a schematic view of the combined swirl and swirling action of the swirl prefilming plate in the staged combustor head with swirl prefilming plate structure shown in FIG. 1.
FIG. 8 is a schematic view of another embodiment of the swirl prefilmer plate in the staged combustor head with swirl prefilmer plate structure shown in FIG. 1.
FIG. 9 is a schematic view of one of the attachment means of the swirl prefilming plate in the staged combustor head with swirl prefilming plate structure shown in FIG. 1.
FIG. 10 is a schematic view of another attachment of the swirl prefilming plate in the staged combustor head with swirl prefilming plate structure shown in FIG. 1.
Reference numerals: 10-main combustion stage; 11-inner ring; 12-a sleeve; 13-the airway; 14-axial swirl vanes; 15-swirl prefilming plate; 151-segmented arc; 152-matching orifice arc ridges; 153-spaced arc ridges; 16-rib plate; 17-inner ring rib plate; 18-a primary combustion stage nozzle; 20-precombustion stage; 21-pre-combustion stage nozzle; 22-a first stage swirl component; 23-secondary cyclone assembly.
Detailed Description
The present disclosure will be described in further detail with reference to the drawings and embodiments. It is to be understood that the specific embodiments described herein are for purposes of illustration only and are not to be construed as limitations of the present disclosure. It should be further noted that, for the convenience of description, only the portions relevant to the present disclosure are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present disclosure may be combined with each other without conflict. The present disclosure will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
According to a first embodiment of the present disclosure, a staged combustion chamber head with a swirl prefilming plate structure is provided, which adopts a central staged structure, including a main combustion stage 10 and a precombustion stage 20, and has an external shape as shown in fig. 1.
As shown in fig. 2, the main combustion stage 10 includes an inner ring 11, axial swirl vanes 14, an swirl prefilming plate 15, and a sleeve 12, the swirl prefilming plate 15 may be formed by welding a plurality of segmented arcs 151, or may be formed by directly cutting a blank by an advanced cutting process, and then the axial swirl vanes 14 and the swirl prefilming plate 15 are welded and combined, and then the combined axial swirl vanes 14 and the swirl prefilming plate 15 are welded to the inner ring 11, and finally the sleeve 12 is welded to form the main combustion stage 10.
The main combustion stage nozzle 18 is inserted into the spray holes of the inner ring 11, the spray holes are uniformly distributed along the circumferential direction, direct injection is carried out on the air passage 13 of the main combustion stage 10, and the injected fuel is matched with the swirl prefilming plate 15 in the air passage 13, so that the effects of improving the atomization quality and improving the combustion and emission performance are achieved.
When the main combustion stage 10 adopts an axial swirling mode, the swirl prefilming plate 15 is arranged along the swirling airflow direction, and plays a role of a certain axial swirling vane 14, as shown in fig. 4. Therefore, the structure of the swirl prefilming plate 15 in this embodiment does not weaken the swirl effect, but enhances the swirl effect generated by the axial swirl vanes 14, and can match swirlers with different swirl numbers.
Directly spout and spout the arc ridge department that the fuel sprayed the plume prefilming plate 15, can form the plume effect along arc ridge both sides respectively under the water conservancy diversion effect of plume prefilming plate 15, compare with prior art, the combustion chamber head in this embodiment is difficult more forms local fuel on the plume prefilming plate 15 and piles up the phenomenon, has reduced oil film thickness, has increased oil film and air area of contact, as shown in fig. 6.
The specific implementation mode of the setting of the rolling flow prefilming plate 15 is as follows:
the number of the segmented arcs 151 of the film pre-winding plate 15 is twice as many as the number of the jet holes. As shown in fig. 3, the geometric characteristic parameters of the swirl prefilming plate 15 include: the swirl prefilming plate comprises an upstream end radial height Ha1 of an arc ridge which is opposite to a spray hole in a matching spray hole arc ridge 152, an upstream end radial height Hb1 of an arc ridge which is opposite to the spray hole in a spacing arc ridge 153, an upstream end arc radius R1, a downstream end radial height Ha2 of the arc ridge 152 of the matching spray hole, a downstream end radial height Hb2 of the spacing arc ridge 153, a downstream end arc radius R2, a swirl prefilming plate 15 thickness S and a swirl prefilming plate 15 axial length L, wherein the upstream end is in the front, the downstream end is in the back, and the axial length refers to the distance in the front-back direction. The curved surface of the arc section of the film rolling pre-coating plate 15 is a three-dimensional curved surface formed by smoothly transiting the arc at the upstream end of the film rolling pre-coating plate 15 to the arc at the downstream end along the streamline and sweeping, as shown in fig. 4, the film rolling pre-coating plates 15 with different shapes can be designed by changing the geometric characteristic parameters of the film rolling pre-coating plate 15, so as to achieve different atomization effects.
Note that the upstream end radial height Ha1 of the matching nozzle hole arc ridges 152, the upstream end radial height Hb1 of the spacing arc ridges 153, the downstream end radial height Ha2 of the matching nozzle hole arc ridges 152, and the downstream end radial height Hb2 of the spacing arc ridges 153 are distances from the end points of the respective arc ridges to the central axis of the inner ring 11, as shown in fig. 3.
In the geometric characteristics of the swirl prefilming plate 15, the upstream end radial height Ha1 of the matching nozzle hole arc ridges 152, the upstream end radial height Hb1 of the spacing arc ridges 153, the downstream end radial height Ha2 of the matching nozzle hole arc ridges 152 and the downstream end radial height Hb2 of the spacing arc ridges 153 are all larger than the radius of the outer surface of the inner ring 11 and smaller than the radius of the inner surface of the sleeve 12. In one embodiment, as shown in FIG. 8, a variable end face radius design, where R1 is not equal to R2, R1 is 8mm, and R2 is 12 mm.
In one embodiment, the axial length of the swirl prefilming plate 15 is 20% to 300% of the axial length of the axial swirl vanes 14. The swirl prefilming plate 15 also has a swirl guiding effect on swirl air, the longer the axial length of the swirl prefilming plate 15 is, the more favorable the swirl is generated, the more sufficient the oil film forms swirl motion, but at the same time, the longer the oil film stays on the swirl prefilming plate 15. Therefore, by changing the axial length of the swirl prefilming plate 15, the swirl and swirl effects, as well as the oil film residence time, are affected, thereby affecting the atomization effect.
In one embodiment, the thickness of the swirl prefilming plate 15 is 20% to 100% of the thickness of the axial swirl vanes 14. The rigidity of the swirl prefilming plate 15 can be changed by changing the thickness of the swirl prefilming plate 15, and the swirl prefilming plate 15 vibrates in different degrees under the impact action of air flow and oil bundles, so that the oil film breaking process can be influenced.
The specific implementation mode of matching the spray holes with the swirl prefilming plate 15 is as follows:
the spray holes are opposite to the arc ridges of the swirl prefilming plate 15, the spray holes are uniformly distributed on the inner ring 11 along the circumferential direction, and one spray hole is arranged at a distance of one arc ridge of the swirl prefilming plate 15 and matched with the arc ridge, as shown in fig. 3 and 6. One way to achieve the matching of the spray holes and the arc ridges is to locate the spray holes on the installation line of the axial swirl vanes 14 of the main combustion stage 10, i.e., the intersection line of the axial swirl vanes 14 and the outer surface of the inner ring 11, thus ensuring the intersection of the spray hole axes and the arc ridges of the swirl prefilming plate 15. After being sprayed out from the spray holes, the fuel oil moves under the combined action of jet flow and air swirl to form primary space atomization in the air passage 13; and then, the fuel oil just moves to the matching spray hole arc ridge 152 of the swirl prefilming plate 15 and is uniformly divided into two oil bundles by the matching spray hole arc ridge 152, the two oil bundles respectively form three-dimensional flow with swirl and swirl along the arc of the swirl prefilming plate 15, the fuel oil with large momentum returns to the center of the air passage 13 along the arc to form secondary space atomization, the fuel oil with small momentum does not separate from the swirl prefilming plate 15, an oil film is formed on the swirl prefilming plate 15 and moves to the downstream end of the swirl prefilming plate 15, so that oil film breaking atomization is formed, and the atomization quality is improved, as shown in fig. 6.
The injection direction of the injection holes can be any direction in the plane of the axial swirl vanes 14, and can be forward inclined, backward inclined or perpendicular to the airflow flowing direction. However, the injection direction should match with the swirl prefilming plate 15, that is, it is required to ensure that the fuel can be injected to the matching injection hole arc ridge 152 of the swirl prefilming plate 15, so as to prevent the fuel from directly injecting out of the air duct 13 without contacting the swirl prefilming plate 15, as shown in fig. 5.
The specific implementation mode of the fixing of the swirl prefilming plate 15 is as follows:
the swirl prefilming plate 15 may be fixed in an end face manner, that is, the front end face of the swirl prefilming plate 15 is welded and fixed to the rear end face of the axial swirl vane 14, and the prefilming plate is only fixed to the front end thereof in this scheme, as shown in fig. 9; or, the rib plate 16 is fixed, that is, the rib plate 16 parallel to the axial swirl blade 14 is welded on the inner surface of the sleeve 12, and the rib plate 16 is welded and fixed with the swirl prefilming plate 15, so that the axial swirl blade 14 and the rib plate 16 can be integrated as a whole, as shown in fig. 2; it is also possible to reduce the number of rib plates 16 when welding and fixing the swirl prefilming plate 15, as shown in fig. 10.
Under the condition of ensuring that the spray holes are matched with the arc ridges of the swirl prefilming plate 15, the fixed welding positions of the swirl prefilming plate 15 can be any circumferential positions, but the welding at the arc ridges is more convenient, and as shown in fig. 7, 9 and 10, the end face fixing or the rib plate 16 fixing is carried out at the arc ridges.
Pre-stage 20 may be implemented using known technology, and in one embodiment, pre-stage 20 may include a pre-stage nozzle 21, a first stage swirler assembly 22, and a second stage swirler assembly 23, pre-stage nozzle 21 being threadably coupled to first stage swirler assembly 22, and first stage swirler assembly 22 being threadably or welded to second stage swirler assembly 23, as shown in FIG. 2. In fig. 2, the first stage swirl component 22 adopts oblique-flow air intake, and the second stage swirl component 23 adopts radial swirl air intake, but other air intake methods are also possible, and the present disclosure does not have any special requirement on the swirl air intake method of the pre-combustion stage 20.
The main combustion stage 10 is connected with the pre-combustion stage 20 by screwing or welding the two-stage swirl component 23 of the pre-combustion stage 20 and the inner ring rib plate 17, as shown in fig. 2, so as to form a head part of the staged combustion chamber with axial swirl and an eddy flow prefilming plate 15 structure of the main combustion stage 10.
In the description herein, reference to the description of the terms "one embodiment/mode," "some embodiments/modes," "example," "specific example," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment/mode or example is included in at least one embodiment/mode or example of the application. In this specification, the schematic representations of the terms used above are not necessarily intended to be the same embodiment/mode or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments/modes or examples. Furthermore, the various embodiments/aspects or examples and features of the various embodiments/aspects or examples described in this specification can be combined and combined by one skilled in the art without conflicting therewith.
Furthermore, 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 implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present application, "plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
It will be understood by those skilled in the art that the foregoing embodiments are provided merely for clarity of explanation and are not intended to limit the scope of the disclosure. Other variations or modifications may occur to those skilled in the art, based on the foregoing disclosure, and are still within the scope of the present disclosure.
Claims (7)
1. A staged combustion chamber head with swirl prefilming plate structure, comprising: the device comprises a pre-combustion stage (20) and a main combustion stage (10) sleeved outside the pre-combustion stage (20);
the main combustion stage (10) comprises an inner ring (11) and a sleeve (12) sleeved outside the inner ring (11);
the inner ring (11) is provided with a plurality of spray holes distributed along the circumferential direction;
an annular air channel (13) is formed between the inner ring (11) and the sleeve (12);
an axial rotational flow blade (14) and a swirl prefilming plate (15) are sequentially arranged in the air passage (13) from front to back;
the axial swirl blades (14) are arranged in a plurality, and the plurality of axial swirl blades (14) are arranged along the circumferential direction;
the swirling flow prefilming plate (15) is annular, and the swirling flow prefilming plate (15) is formed by a plurality of segmented arcs (151) arranged along the circumferential direction;
the spray holes are arranged opposite to the arc ridges of the swirl prefilming plate (15), and two segmented arcs (151) are arranged between any two adjacent spray holes;
the radial heights of the front end and the rear end of the arc ridge are both larger than the radius of the outer surface of the inner ring (11) and smaller than the radius of the inner surface of the sleeve (12);
the front end of the swirl prefilming plate (15) is connected to the tail end of the axial swirl vane (14), or the staged combustion chamber head further comprises: a plurality of webs (16); the inner side and the outer side of each rib plate (16) are respectively connected to the swirl prefilming plate (15) and the sleeve (12); the rib plate (16) and the axial swirl vane (14) are integrally formed.
2. The staged combustor head with a swirl prefilming plate structure as claimed in claim 1, characterized in that the inner side of the web (16) is connected to the swirl prefilming plate (15) at the arc ridge.
3. The staged combustor head with a swirl prefilming plate structure as claimed in claim 1, wherein there are two said segmented arcs (151) between any adjacent two said webs (16).
4. The staged combustor head with swirl prefilming plate structure as claimed in claim 1, wherein said segmented arcs (151) are of unequal diameters at the front and rear ends.
5. The staged combustor head with swirl prefilming plate structure as claimed in claim 1, characterized in that the axial length of the swirl prefilming plate (15) is 20% to 300% of the axial length of the axial swirl vanes (14).
6. The staged combustor head with a swirl prefilming plate structure as claimed in claim 1, characterized in that the thickness of the swirl prefilming plate (15) is 20% to 100% of the thickness of the axial swirl vanes (14).
7. The staged combustion chamber head with swirl prefilming plate structure as claimed in claim 1, characterized in that the precombustion stage (20) comprises: a pre-combustion stage nozzle (21), a first stage swirl component (22) and a second stage swirl component (23);
the pre-combustion stage nozzle (21) is connected with the primary cyclone assembly (22);
the primary cyclone assembly (22) is connected with the secondary cyclone assembly (23);
the secondary swirler assembly (23) is connected to the inner ring (11).
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| CN202110606554.6A CN113280367B (en) | 2021-05-31 | 2021-05-31 | Staged combustion chamber head with swirl pre-membrane plate structure |
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| CN202110606554.6A CN113280367B (en) | 2021-05-31 | 2021-05-31 | Staged combustion chamber head with swirl pre-membrane plate structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115164232B (en) * | 2022-08-18 | 2023-04-25 | 中国航空发动机研究院 | Baffle, baffle assembly and stabilizer |
| CN115164233B (en) * | 2022-08-18 | 2023-04-25 | 中国航空发动机研究院 | Baffle assembly and stabilizer |
| CN115949970B (en) * | 2023-01-05 | 2023-08-22 | 中国航空发动机研究院 | Cyclone blade and cyclone |
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| CN206281002U (en) * | 2015-10-16 | 2017-06-27 | 中航商用航空发动机有限责任公司 | Main combustion stage uses the low pollution combustor of the pre- reverse eddy flow of film radial direction two-stage of individual layer |
| CN206861594U (en) * | 2017-05-25 | 2018-01-09 | 上海泛智能源装备有限公司 | A kind of gas turbine |
| CN108592084A (en) * | 2018-05-17 | 2018-09-28 | 北京航空航天大学 | A kind of main combustion stage matches the low emission combustor head of blade injection structure using the pre- diaphragm plate of axial rotational flow |
| KR20190048904A (en) * | 2017-10-31 | 2019-05-09 | 두산중공업 주식회사 | Fuel nozzle, combustor and gas turbine having the same |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN206281002U (en) * | 2015-10-16 | 2017-06-27 | 中航商用航空发动机有限责任公司 | Main combustion stage uses the low pollution combustor of the pre- reverse eddy flow of film radial direction two-stage of individual layer |
| CN206861594U (en) * | 2017-05-25 | 2018-01-09 | 上海泛智能源装备有限公司 | A kind of gas turbine |
| KR20190048904A (en) * | 2017-10-31 | 2019-05-09 | 두산중공업 주식회사 | Fuel nozzle, combustor and gas turbine having the same |
| CN108592084A (en) * | 2018-05-17 | 2018-09-28 | 北京航空航天大学 | A kind of main combustion stage matches the low emission combustor head of blade injection structure using the pre- diaphragm plate of axial rotational flow |
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