CN116336503B - Combustion chamber unit body structure - Google Patents
Combustion chamber unit body structure Download PDFInfo
- Publication number
- CN116336503B CN116336503B CN202310306109.7A CN202310306109A CN116336503B CN 116336503 B CN116336503 B CN 116336503B CN 202310306109 A CN202310306109 A CN 202310306109A CN 116336503 B CN116336503 B CN 116336503B
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- Prior art keywords
- flame tube
- combustion chamber
- nozzle
- pressure turbine
- mounting edge
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 68
- 239000000295 fuel oil Substances 0.000 claims abstract description 15
- 230000002093 peripheral effect Effects 0.000 claims description 22
- 238000007789 sealing Methods 0.000 claims description 15
- 239000011800 void material Substances 0.000 claims 1
- 239000000446 fuel Substances 0.000 abstract description 14
- 230000008602 contraction Effects 0.000 abstract description 8
- 238000001816 cooling Methods 0.000 description 5
- 239000007789 gas Substances 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 2
- 230000002452 interceptive effect Effects 0.000 description 2
- 230000013011 mating Effects 0.000 description 2
- 238000002679 ablation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008094 contradictory effect Effects 0.000 description 1
- 239000000112 cooling gas Substances 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
Classifications
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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
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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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
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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
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The combustion chamber unit body structure comprises a combustion chamber casing, a flame tube arranged in the combustion chamber casing, a high-pressure turbine guider, a fuel oil main pipe and a nozzle; the high-pressure turbine guide is connected with the inner rear mounting edge of the combustion chamber casing through the inner mounting edge of the high-pressure turbine guide and is connected with the outer rear mounting edge of the combustion chamber casing through the outer mounting edge of the high-pressure turbine guide; the flame tube is connected with the inner rear mounting edge of the combustion chamber casing through the inner rear mounting edge; the rear part of the flame tube is in sliding lap joint with the high-pressure turbine guide; the fuel oil main pipe is arranged on the combustion chamber casing, the nozzle is arranged at the outlet end of the fuel oil main pipe, and the nozzle extends into the head part of the flame tube; a floating structure is arranged between the nozzle and the head of the flame tube. According to the invention, the two ends of the flame tube form the movable connection structure, so that the flame tube can freely expand along the axial direction during working, and the interference between the expansion and contraction of the flame tube and the fuel main pipe and the expansion and contraction of the nozzle during working is avoided, thereby ensuring the working reliability of the flame tube.
Description
Technical Field
The invention relates to the technical field of aeroengines and gas turbines, in particular to a combustion chamber unit structure, which is particularly used for a medium-thrust engine.
Background
The combustion chamber component is generally used in aero-engines, gas turbines and other equipment, and the combustion chamber is mainly used for using high-pressure air from a gas compressor for fuel combustion and heat release, so that the enthalpy value of the high-pressure air is increased, and the working capacity of the high-pressure air for pushing a turbine is improved. The combustor components are typically located in an intermediate position of an aircraft engine, gas turbine, and between the compressor and turbine, some of the axial force between the two needs to be transferred.
In the prior art, as disclosed in patent publication number CN114484498a, a fan-shaped combustion chamber structure is disclosed, the front end of a combustion chamber casing is fixed with a fuel main pipe, the rear end of the fuel main pipe extends into a flame tube, the upper part of the combustion chamber casing is provided with an ignition mechanism, and the lower end of the ignition mechanism extends into the flame tube; cooling holes are distributed on the left and right side walls of the flame tube. Through cooling Kong Buman the left and right sides wall of flame tube, make the cooling gas pass through the cooling hole, form the impact air film at the left and right sides wall of flame tube, not only improved the cooling effect of flame tube, formed good protection effect to the flame tube moreover, avoided the flame tube to produce the ablation. For another example, patent publication No. CN103868099a discloses an aero-engine combustion chamber and an aero-engine thereof, the aero-engine combustion chamber includes an inner casing, an outer casing, a flame tube, a fuel nozzle, and a multi-channel inlet diffuser, the rear end of the fuel nozzle is disposed on the flame tube head, and fuel enters the flame tube head through the fuel nozzle.
In the prior art, the nozzle is connected through the fuel oil main pipe and is inserted into the front end of the flame tube, and the rear end of the flame tube is connected in a fixed connection mode. In the existing combustion chamber structure, the flame tube cannot expand freely along the axial direction of the flame tube after being heated, and the flame tube is easy to interfere with the electric nozzle bushing assembly and the nozzle in the working process.
Disclosure of Invention
The main purpose of the present invention is to provide a combustion chamber unit structure, which aims to solve the above technical problems.
In order to achieve the above purpose, the present invention provides a combustion chamber unit structure, which comprises a combustion chamber casing, a flame tube arranged inside the combustion chamber casing, a high-pressure turbine guide, a fuel oil main pipe and a nozzle; the high-pressure turbine guide is connected with the inner rear mounting edge of the combustion chamber casing through the inner mounting edge of the high-pressure turbine guide and is connected with the outer rear mounting edge of the combustion chamber casing through the outer mounting edge of the high-pressure turbine guide; the flame tube is connected with the inner rear mounting edge of the combustion chamber casing through the inner rear mounting edge; the rear part of the flame tube is in sliding lap joint with the high-pressure turbine guide; the fuel oil main pipe is arranged on the combustion chamber casing, the nozzle is arranged at the outlet end of the fuel oil main pipe, and the nozzle extends into the head part of the flame tube; a floating structure is arranged between the nozzle and the head of the flame tube.
Preferably, a corrugated ring is provided between the outer mounting edge of the high pressure turbine guide and the outer aft mounting edge of the combustor casing.
Preferably, the burner sleeve further comprises a burner sleeve, wherein the upper end of the burner sleeve is installed on the combustion chamber casing, the lower end of the burner sleeve extends into the flame tube, and a gap exists between the peripheral surface of the lower end of the burner sleeve and the flame tube.
Preferably, the floating structure is a floating ring arranged at the head part of the flame tube, and the inner ring surface of the floating ring is in sliding fit with the outer peripheral surface of the nozzle.
Preferably, a plurality of empty slots are uniformly distributed on the inner ring surface of the floating ring.
Preferably, the floating structure is a vortex device arranged at the head part of the flame tube, and the inner hole surface of the vortex device is in sliding fit with the outer peripheral surface of the nozzle.
Preferably, a plurality of concave grooves are uniformly distributed on the inner hole surface of the vortex device.
Preferably, a sealing honeycomb structure is provided on the high pressure turbine guide.
Preferably, an adjusting gasket is arranged between the sealed honeycomb structure and the high-pressure turbine guide, and the adjusting gasket is of a sleeve structure with an eccentric space; the adjusting gasket, the high-pressure turbine guide and the sealed honeycomb structure are connected to the inner rear mounting edge of the combustor casing through screws and locking plates.
Preferably, a first positioning surface and a second positioning surface are arranged on the high-pressure turbine guide, and the rear part of the flame tube is in sliding lap joint with the first positioning surface and the second positioning surface.
Due to the adoption of the technical scheme, the invention has the following beneficial effects:
(1) According to the invention, the floating structure is arranged between the nozzle and the head of the flame tube, and the rear part of the flame tube is in sliding lap joint with the high-pressure turbine guide, so that the two ends of the flame tube form a movable connection structure, and when the flame tube works, the flame tube can freely expand along the axial direction, and the flame tube, the fuel oil main pipe and the nozzle can not interfere with each other due to expansion and contraction of cold during the working process, so that the working reliability of the flame tube is ensured. Effectively solves the problems that in the prior art, two ends of the flame tube are connected in a fixed mode, and the flame tube cannot expand freely along the axial direction and is easy to interfere when working.
(2) In the invention, the floating structure adopts the floating ring or the vortex device, the inner ring surface of the floating ring is in sliding fit with the outer peripheral surface of the nozzle, and the inner hole surface of the vortex device is in sliding fit with the outer peripheral surface of the nozzle, so that floating between the nozzle and the head of the flame tube is effectively realized during working, the flame tube can freely expand along the axial direction, and interference caused by heat expansion and cold contraction is avoided during working.
(3) In the invention, the corrugated ring is arranged between the outer mounting edge of the high-pressure turbine guide and the outer rear mounting edge of the combustion chamber casing, and the corrugated ring has certain elasticity, so that the high-pressure turbine guide and the combustion chamber casing can be assembled in a coordinated manner, and the corrugated ring can shrink when the flame tube expands freely along the axial direction, so that interference between the flame tube and the high-pressure turbine guide when the flame tube expands is avoided.
(4) In the invention, because a gap exists between the peripheral surface of the lower end of the electric nozzle bushing and the flame tube, the flame tube is ensured not to interfere with the electric nozzle bushing due to heat expansion and cold contraction during working.
(6) In the invention, a plurality of hollow grooves are uniformly distributed on the inner ring surface of the floating ring, and a plurality of concave grooves are uniformly distributed on the inner hole surface of the vortex device, so that the aim of reducing the contact surface between the outer peripheral surface of the nozzle and the inner ring surface of the floating ring or between the outer peripheral surface of the nozzle and the inner hole surface of the vortex device is achieved, firstly, sliding friction is reduced, and secondly, when the nozzle extrudes the inner peripheral surfaces of the floating ring and the vortex device due to high-temperature expansion, the hollow grooves and the concave grooves form a yielding space, and the sliding fit of the floating ring, the vortex device and the outer peripheral surface of the nozzle is effectively ensured.
(7) According to the invention, the sealing honeycomb structure is arranged and is used for being matched with the external sealing comb teeth, and the surface F on the sealing honeycomb structure is used for adjusting the runout with the central line formed by the circumferentially arranged holes D of the combustion chamber casing as a reference through changing the adjusting gasket, so that the sealing gap is ensured.
(8) The combustion chamber unit body structure provided by the invention has the advantages of compact structure and light weight, and the expansion and contraction of each part in the combustion chamber during working are considered, so that the connection reliability and the working stability of the parts are ensured.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to the structures shown in these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of an ignition section of a combustion chamber unit structure according to an embodiment of the present invention;
FIG. 2 is a schematic non-ignition cross-sectional view of a combustion chamber unit structure according to a second embodiment of the present invention;
FIG. 3 is a schematic view of the circumferential position distribution of the tip liner in the combustor unit structure of the present invention;
FIG. 4 is a front view of the floating ring of the present invention;
FIG. 5 is a cross-sectional view taken along section A-A of FIG. 4;
FIG. 6 is a front view of an adjustment shim according to the present invention;
Fig. 7 is a cross-sectional view taken along section B-B in fig. 6.
Reference numerals illustrate: 1. a fuel manifold; 2. a tip bushing; 3. a flame tube; 4. a combustion chamber casing; 5. a high pressure turbine guide; 6. screw and locking plate; 7. a floating ring; 701. slotting in the air; 8. a corrugated ring; 9. sealing the honeycomb structure; 10. adjusting the gasket; 11. a nozzle; 12. a swirler; 13. and a gas-introducing hole.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It should be noted that all directional indicators (such as up, down, left, right, front, and rear … …) in the embodiments of the present invention are merely used to explain the relative positional relationship, movement, etc. between the components in a particular posture (as shown in the drawings), and if the particular posture is changed, the directional indicator is changed accordingly.
Furthermore, the description of "first," "second," etc. in this disclosure is for descriptive purposes only and is not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In addition, the technical solutions of the embodiments may be combined with each other, but it is necessary to base that the technical solutions can be realized by those skilled in the art, and when the technical solutions are contradictory or cannot be realized, the combination of the technical solutions should be considered to be absent and not within the scope of protection claimed in the present invention.
Example 1
Referring to fig. 1,3 to 7, a first embodiment of a combustion chamber unit structure provided by the present invention, specifically, the combustion chamber unit structure includes a combustion chamber casing 4, a flame tube 3 disposed inside the combustion chamber casing 4, and further includes a high pressure turbine guide 5, a fuel manifold 1, and a nozzle 11; the high-pressure turbine guide 5 is connected with the inner rear mounting edge of the combustor casing 4 through the inner mounting edge thereof and is connected with the outer rear mounting edge of the combustor casing 4 through the outer mounting edge thereof, specifically, a first positioning surface A and a second positioning surface B are arranged on the high-pressure turbine guide 5, and the rear part of the flame tube 3 is in sliding lap joint with the first positioning surface A and the second positioning surface B; the flame tube 3 is connected with the inner rear mounting edge of the combustion chamber casing 4 through the inner rear mounting edge; the rear part of the flame tube 3 is in sliding lap joint with the high-pressure turbine guide 5; the fuel oil main pipe 1 is arranged on the combustion chamber casing 4 through a plurality of pins which are circumferentially arranged, the nozzle 11 is arranged at the outlet end of the fuel oil main pipe 1, and the nozzle 11 extends into the head of the flame tube 3; a floating structure is provided between the nozzle 11 and the head of the flame tube 3.
Through adopting being provided with floating structure between nozzle 11 and the head of flame tube 3 to and through the rear portion slip overlap joint of flame tube 3 on high-pressure turbine director 5, make the both ends of flame tube 3 form swing joint structure, at the during operation, flame tube 3 can freely expand along the axial, guarantees that flame tube 3 and fuel house steward 1 and nozzle 11's expend with heat and contract with cold can not produce the interference in the course of the operation. Effectively solves the problems that in the prior art, two ends of the flame tube are connected in a fixed mode, and the flame tube cannot expand freely along the axial direction and is easy to interfere when working.
Further, as shown in connection with fig. 1, in the present embodiment, a corrugated ring 8 is provided between the outer mounting edge of the high-pressure turbine guide 5 and the outer rear mounting edge of the combustor casing 4. Because the ripple ring 8 has certain elasticity, firstly, the coordinated assembly size between the high-pressure turbine guide 5 and the combustor casing 4 is convenient, and secondly, when the flame tube 3 freely expands along the axial direction, the ripple ring 8 can shrink, so that interference with the high-pressure turbine guide 5 when the flame tube 3 expands is avoided.
As shown in fig. 1, the combustion chamber unit body structure further comprises an electric nozzle liner 2, wherein the upper end of the electric nozzle liner 2 is installed on the combustion chamber casing 4, the lower end of the electric nozzle liner 2 extends into the flame tube 3, and a gap exists between the peripheral surface of the lower end of the electric nozzle liner 2 and the flame tube 3. Therefore, the flame tube 3 is ensured not to interfere with the electric nozzle lining 2 due to heat expansion and cold contraction during working. Specifically, the upper end of the electric nozzle bush 2 is fixed on the combustion chamber casing 4 through a screw, the design clearance between the electric nozzle bush 2 and the flame tube 3 is N1 and N2, the design clearance is N1 and N2 through adjusting the mounting screw of the electric nozzle bush 2, and the flame tube 3 and the electric nozzle bush 2 are prevented from interfering in the working process.
In this embodiment, the floating structure is a floating ring 7 mounted on the head of the flame tube 3, and the inner ring surface of the floating ring 7 is in sliding fit with the outer peripheral surface of the nozzle 11. As shown in fig. 4 and 5, a plurality of hollow slots 701 are uniformly distributed on the inner ring surface of the floating ring 7, so as to reduce the contact surface between the outer peripheral surface of the nozzle 11 and the inner ring surface of the floating ring 7, firstly reduce sliding friction, and secondly form a relief space when the nozzle 11 extrudes the inner peripheral surface of the floating ring 7 due to high-temperature expansion, so that the sliding fit between the floating ring 7 and the outer peripheral surface of the nozzle 11 is effectively ensured.
In this embodiment, a sealing honeycomb structure 9 is provided on the high pressure turbine guide 5 for mating with an external sealing comb. Specifically, an adjusting gasket 10 is arranged between the sealed honeycomb structure 9 and the high-pressure turbine guide 5, and the adjusting gasket 10 is of a sleeve structure with an eccentric space; the adjusting shim 10, the high-pressure turbine guide 5 and the sealing honeycomb structure 9 are connected together to the inner rear mounting edge of the combustor casing 4 by screws and locking pieces 6. The face F on the seal honeycomb structure 9 is adjusted by changing the adjusting shim 10 to adjust the runout with the center line formed by the circumferentially arranged holes D of the combustor casing 4 as a reference, ensuring the seal clearance.
As shown in connection with fig. 1, bleed air holes 13 (i.e. holes E in the figure) are provided in the high-pressure turbine pilot 5 for achieving turbine cooling of the bleed air.
As shown in connection with fig. 3, the electric tip liner 2 is located in the upper semicircle of the combustion chamber, so that the structure is more compact.
Example two
Based on the first embodiment, referring to fig. 2, 3 and fig. 6 and 7, a second embodiment of a combustion chamber unit structure provided by the present invention, specifically, the combustion chamber unit structure includes a combustion chamber casing 4, a flame tube 3 disposed inside the combustion chamber casing 4, and further includes a high-pressure turbine guide 5, a fuel header pipe 1, and a nozzle 11; the high-pressure turbine guide 5 is connected with the inner rear mounting edge of the combustor casing 4 through the inner mounting edge thereof and is connected with the outer rear mounting edge of the combustor casing 4 through the outer mounting edge thereof, specifically, a first positioning surface A and a second positioning surface B are arranged on the high-pressure turbine guide 5, and the rear part of the flame tube 3 is in sliding lap joint with the first positioning surface A and the second positioning surface B; the flame tube 3 is connected with the inner rear mounting edge of the combustion chamber casing 4 through the inner rear mounting edge; the rear part of the flame tube 3 is in sliding lap joint with the high-pressure turbine guide 5; the fuel oil main pipe 1 is arranged on the combustion chamber casing 4 through a plurality of pins which are circumferentially arranged, the nozzle 11 is arranged at the outlet end of the fuel oil main pipe 1, and the nozzle 11 extends into the head of the flame tube 3; a floating structure is provided between the nozzle 11 and the head of the flame tube 3.
Through adopting being provided with floating structure between nozzle 11 and the head of flame tube 3 to and through the rear portion slip overlap joint of flame tube 3 on high-pressure turbine director 5, make the both ends of flame tube 3 form swing joint structure, at the during operation, flame tube 3 can freely expand along the axial, guarantees that flame tube 3 and fuel house steward 1 and nozzle 11's expend with heat and contract with cold can not produce the interference in the course of the operation. Effectively solves the problems that in the prior art, two ends of the flame tube are connected in a fixed mode, and the flame tube cannot expand freely along the axial direction and is easy to interfere when working.
In the present embodiment, a corrugated ring 8 is provided between the outer mounting edge of the high-pressure turbine guide 5 and the outer rear mounting edge of the combustor casing 4. Because the ripple ring 8 has certain elasticity, firstly, the coordinated assembly size between the high-pressure turbine guide 5 and the combustor casing 4 is convenient, and secondly, when the flame tube 3 freely expands along the axial direction, the ripple ring 8 can shrink, so that interference with the high-pressure turbine guide 5 when the flame tube 3 expands is avoided.
The combustion chamber unit body structure further comprises an electric nozzle liner 2, wherein the upper end of the electric nozzle liner 2 is arranged on the combustion chamber casing 4, the lower end of the electric nozzle liner 2 extends into the flame tube 3, and a gap exists between the peripheral surface of the lower end of the electric nozzle liner 2 and the flame tube 3. Therefore, the flame tube 3 is ensured not to interfere with the electric nozzle lining 2 due to heat expansion and cold contraction during working. Specifically, the upper end of the electric nozzle bush 2 is fixed on the combustion chamber casing 4 through a screw, the design clearance between the electric nozzle bush 2 and the flame tube 3 is N1 and N2, the design clearance is N1 and N2 through adjusting the mounting screw of the electric nozzle bush 2, and the flame tube 3 and the electric nozzle bush 2 are prevented from interfering in the working process.
In this embodiment, the floating structure is a swirler 12 mounted on the head of the flame tube 3, the inner hole surface of the swirler 12 is in sliding fit with the outer peripheral surface of the nozzle 11, a plurality of concave grooves (not shown in the figure) are uniformly distributed on the inner hole surface of the swirler 12, the swirler 12 plays a role in swirl divergence on fuel sprayed from the nozzle 11, and by arranging the concave grooves, the purpose is to reduce the contact surface between the outer peripheral surface of the nozzle 11 and the inner hole surface of the swirler 12, firstly, the sliding friction is reduced, secondly, when the nozzle 11 forms extrusion on the inner hole surface of the swirler 12 due to high-temperature expansion, the concave grooves form a yielding space, so that the sliding fit between the swirler 12 and the outer peripheral surface of the nozzle 11 is effectively ensured.
In this embodiment, a sealing honeycomb structure 9 is provided on the high pressure turbine guide 5 for mating with an external sealing comb. Specifically, an adjusting gasket 10 is arranged between the sealed honeycomb structure 9 and the high-pressure turbine guide 5, and the adjusting gasket 10 is of a sleeve structure with an eccentric space; the adjusting shim 10, the high-pressure turbine guide 5 and the sealing honeycomb structure 9 are connected together to the inner rear mounting edge of the combustor casing 4 by screws and locking pieces 6. The face F on the seal honeycomb structure 9 is adjusted by changing the adjusting shim 10 to adjust the runout with the center line formed by the circumferentially arranged holes D of the combustor casing 4 as a reference, ensuring the seal clearance.
The foregoing description is only of the preferred embodiments of the present invention, and is not intended to limit the scope of the invention, but rather, the equivalent structural changes made by the description of the present invention and the accompanying drawings or the direct/indirect application in other related technical fields are included in the scope of the invention.
Claims (6)
1. The combustion chamber unit body structure comprises a combustion chamber casing (4) and a flame tube (3) arranged inside the combustion chamber casing (4), and is characterized by further comprising a high-pressure turbine guide (5), a fuel oil main pipe (1) and a nozzle (11);
the high-pressure turbine guide (5) is connected with the inner rear mounting edge of the combustion chamber casing (4) through the inner mounting edge and is connected with the outer rear mounting edge of the combustion chamber casing (4) through the outer mounting edge;
The flame tube (3) is connected with the inner rear mounting edge of the combustion chamber casing (4) through the inner rear mounting edge; the rear part of the flame tube (3) is in sliding lap joint with the high-pressure turbine guide (5);
the fuel oil main pipe (1) is arranged on the combustion chamber casing (4), the nozzle (11) is arranged at the outlet end of the fuel oil main pipe (1), and the nozzle (11) extends into the head of the flame tube (3);
a floating structure is arranged between the nozzle (11) and the head of the flame tube (3);
the burner comprises a burner sleeve (2), wherein the upper end of the burner sleeve (2) is arranged on a combustion chamber casing (4), the lower end of the burner sleeve extends into a flame tube (3), and a gap exists between the peripheral surface of the lower end of the burner sleeve (2) and the flame tube (3);
The floating structure is a floating ring (7) arranged at the head of the flame tube (3), the inner ring surface of the floating ring (7) is in sliding fit with the outer peripheral surface of the nozzle (11), and a plurality of empty slots (701) are uniformly distributed on the inner ring surface of the floating ring (7);
a corrugated ring (8) is arranged between the outer mounting edge of the high-pressure turbine guide (5) and the outer rear mounting edge of the combustor casing (4).
2. A combustion chamber unit structure as claimed in claim 1, wherein the floating structure is a swirler (12) mounted on the head of the flame tube (3), and an inner hole surface of the swirler (12) is slidably fitted to the outer peripheral surface of the nozzle (11).
3. A combustion chamber unit structure as claimed in claim 2, characterized in that a plurality of concave grooves are uniformly distributed on the inner bore surface of the swirler (12).
4. A combustion chamber unit structure according to claim 1, characterized in that a sealing honeycomb structure (9) is provided on the high-pressure turbine guide (5).
5. A combustion chamber unit structure according to claim 4, characterized in that an adjusting gasket (10) is arranged between the sealing honeycomb structure (9) and the high-pressure turbine guide (5), the adjusting gasket (10) being of a sleeve structure with an eccentric void;
The adjusting gasket (10), the high-pressure turbine guide (5) and the sealing honeycomb structure (9) are connected to the inner rear mounting edge of the combustor casing (4) through screws and locking plates (6) together.
6. A combustion chamber unit structure as claimed in claim 1, wherein the high pressure turbine guide (5) is provided with a first positioning surface (a) and a second positioning surface (B), and the rear part of the flame tube (3) is slidably overlapped on the first positioning surface (a) and the second positioning surface (B).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310306109.7A CN116336503B (en) | 2023-03-27 | 2023-03-27 | Combustion chamber unit body structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310306109.7A CN116336503B (en) | 2023-03-27 | 2023-03-27 | Combustion chamber unit body structure |
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| CN116336503A CN116336503A (en) | 2023-06-27 |
| CN116336503B true CN116336503B (en) | 2024-05-10 |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103868095A (en) * | 2012-12-14 | 2014-06-18 | 中航商用航空发动机有限责任公司 | Active air flow control and adjustment device and engine combustion chamber including same |
| CN106287814A (en) * | 2016-09-29 | 2017-01-04 | 南京航空航天大学 | A kind of ground gas turbine can burner of axial admission |
| CN114017797A (en) * | 2021-10-22 | 2022-02-08 | 清研新能源汽车工程中心（襄阳）有限公司 | Novel oil-gas mixing device |
| CN115046226A (en) * | 2022-08-11 | 2022-09-13 | 成都中科翼能科技有限公司 | Gas turbine flame tube supporting and positioning structure |
| CN115507391A (en) * | 2022-09-16 | 2022-12-23 | 中国航发湖南动力机械研究所 | Ceramic-based flame tube |
| CN115597090A (en) * | 2021-07-09 | 2023-01-13 | 中国航发商用航空发动机有限责任公司（Cn） | Flame tube outlet connecting structure, combustion chamber and gas turbine engine |
-
2023
- 2023-03-27 CN CN202310306109.7A patent/CN116336503B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103868095A (en) * | 2012-12-14 | 2014-06-18 | 中航商用航空发动机有限责任公司 | Active air flow control and adjustment device and engine combustion chamber including same |
| CN106287814A (en) * | 2016-09-29 | 2017-01-04 | 南京航空航天大学 | A kind of ground gas turbine can burner of axial admission |
| CN115597090A (en) * | 2021-07-09 | 2023-01-13 | 中国航发商用航空发动机有限责任公司（Cn） | Flame tube outlet connecting structure, combustion chamber and gas turbine engine |
| CN114017797A (en) * | 2021-10-22 | 2022-02-08 | 清研新能源汽车工程中心（襄阳）有限公司 | Novel oil-gas mixing device |
| CN115046226A (en) * | 2022-08-11 | 2022-09-13 | 成都中科翼能科技有限公司 | Gas turbine flame tube supporting and positioning structure |
| CN115507391A (en) * | 2022-09-16 | 2022-12-23 | 中国航发湖南动力机械研究所 | Ceramic-based flame tube |
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| CN116336503A (en) | 2023-06-27 |
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