An experimental device for detecting the performance of a gas turbine combustion chamber nozzle

Abstract

The present invention discloses a test device for detecting the performance of a gas turbine combustion chamber nozzle. The test device for detecting the performance of a gas turbine combustion chamber nozzle includes an air intake part, a reverse rectification part, and a combustion part. The air intake part supplies the combustion-supporting gas to enter. The reverse rectification part includes a first chamber, a second chamber, and a nozzle installation part. The first chamber is arranged downstream of the second chamber. The first chamber is communicated with the second chamber. The second chamber is communicated with the air intake part. The flow direction of the combustion-supporting gas in the first chamber is opposite to the flow direction of the combustion-supporting gas in the second chamber. The nozzle installation part is used for installing a nozzle through which fuel flows. The combustion part is communicated with the first chamber and is used for being communicated with the nozzle. The test device for detecting the performance of a gas turbine combustion chamber nozzle according to the embodiment of the present invention has the advantages of high reliability and the like.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbine combustion, and particularly relates to a test device for detecting the performance of a nozzle in a gas turbine combustor. Background Art

[0002] The research and development of gas turbine combustors cannot do without combustor tests. Among them, the nozzle performance test is the most basic means to verify the feasibility of the combustion system design. In related technologies, the test device for detecting the performance of a gas turbine combustor nozzle cannot simulate the fluid dynamic process at the nozzle inlet under real conditions, and there are problems such as low reliability of the test data of the combustor nozzle. Summary of the Invention

[0003] The present invention is made based on the inventor's discovery and recognition of the following facts and problems:

[0004] A gas turbine is a rotary internal combustion engine, mainly including a compressor, a combustor, and a turbine. Air flows backward through the compressor exhaust cavity and enters the annular combustor, then enters the premixing cavity of the fuel nozzle. After fuel is injected and mixed with air, it enters the flame tube in the combustor for combustion, and the high-temperature gas is discharged through the transition section.

[0005] The research and development of gas turbine combustors involve both microscale chemical kinetics and macroscopic turbulent flow, and the strong nonlinear coupling between the two. At present, the existing combustion theories and methods are difficult to accurately quantitatively analyze the working characteristics of combustors under real environmental conditions, including ignition characteristics, stable boundaries, combustion efficiency, structural integrity, etc. Therefore, to achieve the comprehensive optimal design results of low NOx emissions, low combustion pulsation, wide working boundaries, and long life, multiple rounds of design optimization iterations are required, and the design scheme is verified and confirmed through means such as numerical simulation and experimental testing. Experiments are the ultimate standard for testing the correctness of the design. Through single-nozzle test research, the nozzle design criteria and test verification techniques can be mastered, and the preliminary design of the combustor nozzle can be completed, the nozzle can be optimized, and the nozzle design scheme can be improved.

[0006] The test device for the nozzle needs to simulate the fluid dynamic process at the nozzle inlet under real conditions to form the required air flow structure. At present, in related technologies, the nozzle test device can only simulate the radial or axial entry of air into the combustor inlet, and cannot simulate the backward reverse flow of air into the combustor inlet. Different nozzle inlet environments will lead to significant differences in the fuel-air mixing and distribution of the nozzle compared with the actual combustor.

[0007] The present invention aims to solve at least one of the technical problems in the related technologies to a certain extent.

[0008] To this end, an embodiment of the present invention provides a test device for detecting the performance of a combustor nozzle of a gas turbine to improve the reliability of test data of the combustor nozzle.

[0009] A test device for detecting the performance of a combustor nozzle of a gas turbine according to an embodiment of the present invention includes an air intake part, a reverse rectification part, and a combustion part. The air intake part allows the combustion-supporting gas to enter. The reverse rectification part includes a first chamber, a second chamber, and a nozzle mounting part. The first chamber is provided downstream of the second chamber. The first chamber communicates with the second chamber. The second chamber communicates with the air intake part. The flow direction of the combustion-supporting gas in the first chamber is opposite to the flow direction of the combustion-supporting gas in the second chamber. The nozzle mounting part is used to mount a nozzle through which fuel flows. The combustion part communicates with the first chamber and is used to communicate with the nozzle so that the combustion-supporting gas and the fuel are mixed and burned to form high-temperature gas.

[0010] A test device for detecting the performance of a combustor nozzle of a gas turbine according to an embodiment of the present invention has advantages such as high reliability.

[0011] In some embodiments, both the first chamber and the second chamber are annular chambers.

[0012] In some embodiments, the reverse rectification part includes a first cylinder, a second cylinder, and an annular first sealing plate. The second cylinder is sleeved outside the first cylinder. The second cylinder and the first cylinder are spaced apart in the inner and outer directions so that the first cylinder and the second cylinder define the second chamber. The first cylinder has a first port and a second port opposite to each other in its extending direction. The second cylinder has a third port and a fourth port opposite to each other in its extending direction.

[0013] The first sealing plate seals the first port. The first sealing plate has a first inner hole through which at least a part of the nozzle passes so that the first cylinder and the nozzle define the first chamber.

[0014] Wherein, the third port is arranged closer to the first sealing plate than the fourth port in the extending direction of the first cylinder. The first port and the third port are arranged staggeredly in the extending direction of the first cylinder so that the first chamber and the second chamber are connected.

[0015] In some embodiments, a third chamber communicating with the second chamber is further included. The third chamber is provided upstream of the second chamber. The third chamber communicates with the air intake part. The flow direction of the combustion-supporting gas in the third chamber intersects with the flow direction of the combustion-supporting gas in the second chamber.

[0016] In some embodiments, the reverse rectification part further includes a third cylinder, an annular second sealing plate, and an annular third sealing plate.

[0017] The third cylinder is sleeved outside the first cylinder. The third cylinder and the first cylinder are spaced apart in the inner and outer directions. The inner diameter of the third cylinder is greater than the inner diameter of the second cylinder. The third cylinder and the second cylinder are arranged along the extending direction of the first cylinder. The third cylinder is disposed upstream of the second cylinder. The third cylinder has a fifth port and a sixth port that are opposite to each other in its extending direction. The fifth port is closer to the fourth port than the sixth port in the extending direction of the first cylinder.

[0018] The second sealing plate and the third sealing plate are spaced apart along the extending direction of the first cylinder. The outer end of the second sealing plate is connected to the third cylinder. The inner end of the second sealing plate is connected to the second cylinder. The outer end of the third sealing plate is connected to the third cylinder. The inner end of the third sealing plate is connected to the first cylinder. So as to define a transition chamber between the third cylinder, the first cylinder, the second sealing plate, and the third sealing plate. The transition chamber is disposed downstream of the third chamber and upstream of the second chamber.

[0019] In some embodiments, the reverse rectification part further includes an annular flow equalizing plate. The flow equalizing plate is disposed in the transition chamber. The flow equalizing plate has a plurality of ventilation holes for the combustion-supporting gas to flow through.

[0020] In some embodiments, the third cylinder has an opening communicating with the intake part. The flow equalizing plate is inclined gradually from the outside to the inside in a direction closer to the first cylinder.

[0021] In some embodiments, the outer end of the flow equalizing plate is connected to at least one of the inner end of the second sealing plate or the second cylinder. The inner end of the flow equalizing plate is connected to at least one of the inner end of the third sealing plate and the first cylinder.

[0022] In some embodiments, the reverse rectification part further includes a fourth chamber. The fourth chamber is disposed upstream of the third chamber. The fourth chamber communicates with the third chamber and the intake part respectively. The flow direction of the combustion-supporting gas in the fourth chamber intersects with the flow direction of the combustion-supporting gas in the third chamber.

[0023] In some embodiments, the reverse rectification part further includes a fifth chamber. The fifth chamber is disposed upstream of the fourth chamber. The flow direction of the combustion-supporting gas in the fifth chamber intersects with the flow direction of the combustion-supporting gas in the fourth chamber. The fifth chamber communicates with the fourth chamber and the intake part respectively.

[0024] In some embodiments, the extending direction of the third chamber is perpendicular to that of the second chamber, so that the flow direction of the combustion-supporting gas in the third chamber is perpendicular to that in the second chamber; and / or the extending direction of the fourth chamber is perpendicular to that of the third chamber, so that the flow direction of the combustion-supporting gas in the fourth chamber is perpendicular to that in the third chamber; and / or the extending direction of the fifth chamber is perpendicular to that of the fourth chamber, so that the flow direction of the combustion-supporting gas in the fifth chamber is perpendicular to that in the fourth chamber.

[0025] In some embodiments, it further includes a combustion-supporting gas pipeline, which is arranged upstream of the second chamber. The combustion-supporting gas pipeline includes a first pipe section, a second pipe section and a third pipe section connected in sequence. The second pipe section is arranged upstream of the first pipe section, and the third pipe section is arranged upstream of the second pipe section. The first pipe section defines the third chamber, the second pipe section defines the fourth chamber, and the third pipe section defines the fifth chamber.

[0026] In some embodiments, there are multiple combustion-supporting gas pipelines, and the multiple combustion-supporting gas pipelines are arranged at intervals along the circumferential direction of the nozzle mounting portion.

[0027] In some embodiments, the air inlet part is an air inlet pipe, and each combustion-supporting gas pipeline is communicated with the air inlet pipe. The multiple combustion-supporting gas pipelines are arranged around the central axis of the air inlet pipe.

[0028] In some embodiments, the combustion part is a combustion pipe, and at least a part of the combustion pipe extends into the first cylinder body so that the first chamber is communicated with the combustion part.

[0029] In some embodiments, the combustion pipe includes a large-diameter section and a small-diameter section. The large-diameter section is arranged downstream of the small-diameter section, and the small-diameter section extends into the first cylinder body. Description of the Drawings

[0030] Figure 1 is the front view of a test device for detecting the performance of a gas turbine combustion chamber nozzle according to an embodiment of the present invention.

[0031] Figure 2 is Figure 1 the enlarged view of part A in

[0032] Figure 3 is the right view of a test device for detecting the performance of a gas turbine combustion chamber nozzle according to an embodiment of the present invention.

[0033] Reference Signs:

[0034] An experimental device 100 for detecting the performance of a nozzle of a gas turbine combustion chamber;

[0035] The intake part 1;

[0036] The reverse rectification part 2; the first chamber 201; the second chamber 202; the third chamber 203; the nozzle mounting part 204; the first cylinder 205; the first port 2051; the second port 2052; the second cylinder 206; the third port 2061; the fourth port 2062; the first sealing plate 207; the first inner hole 2071; the third cylinder 208; the fifth port 2081; the sixth port 2082; the second sealing plate 209; the third sealing plate 210; the transition chamber 211; the flow equalizing plate 212; the ventilation holes 213; the fourth chamber 214; the fifth chamber 215;

[0037] The combustion part 3; the small diameter section 301; the large diameter section 302;

[0038] The nozzle 4; the nozzle orifice 401;

[0039] The combustion supporting gas pipeline 5; the first pipe section 501; the second pipe section 502; the third pipe section 503. Detailed implementation manners

[0040] The embodiments of the present invention will be described in detail below. The examples of the embodiments are shown in the drawings. The embodiments described below with reference to the drawings are exemplary and are intended to explain the present invention, and should not be construed as limiting the present invention.

[0041] The technical solutions of the present application will be described in detail below with reference to the drawings.

[0042] As Figures 1 to 3 shown, an experimental device 100 for detecting the performance of a nozzle of a gas turbine combustion chamber according to an embodiment of the present invention includes an intake part 1, a reverse rectification part 2 and a combustion part 3.

[0043] The intake part 1 allows the combustion supporting gas to enter. The reverse rectification part 2 includes a first chamber 201, a second chamber 202 and a nozzle mounting part 204. The first chamber 201 is provided downstream of the second chamber 202. The second chamber 202 is communicated with the intake part 1. The flow direction of the combustion supporting gas in the first chamber 201 is opposite to the flow direction of the combustion supporting gas in the second chamber 202. The nozzle mounting part 204 is used to mount the nozzle 4 through which the fuel flows.

[0044] The combustion part 3 is communicated with the first chamber 201 and is used to be communicated with the nozzle 4 so that the combustion supporting gas and the fuel are mixed and burned to form high-temperature gas.

[0045] For example, as Figure 1 and Figure 2As shown, the combustion-supporting gas enters the second chamber 202 through the intake part 1, and the combustion-supporting gas entering the second chamber 202 then enters the first chamber 201. Since the flow direction of the combustion-supporting gas in the second chamber 202 is opposite to that in the first chamber 201, that is to say, the combustion-supporting gas entering the second chamber 202 enters the first chamber 201 along the opposite flow direction, thus realizing the reverse rectification of the combustion-supporting gas by the reverse rectification part 2. The combustion-supporting gas entering the first chamber 201 is mixed with the fuel ejected from the nozzle 4 and burns in the combustion part 3 to form high-temperature gas.

[0046] Therefore, in an embodiment of the present invention, a test device 100 for detecting the performance of a nozzle of a gas turbine combustion chamber, after setting the reverse rectification part 2 to perform reverse rectification on the combustion-supporting gas entering the reverse rectification part 2, mixes it with the fuel ejected from the nozzle 4. Compared with the combustion-supporting gas in the related art test device entering the combustion chamber radially or axially along the combustion chamber, it truly simulates the air flow structure at the nozzle 4, maintains the consistency between the test conditions of the nozzle 4 and the actual working environment of the gas turbine, improves the accuracy of the nozzle 4 performance test data, and thus makes the test device 100 for detecting the performance of a nozzle of a gas turbine combustion chamber in an embodiment of the present invention highly reliable.

[0047] Therefore, a test device 100 for detecting the performance of a nozzle of a gas turbine combustion chamber in an embodiment of the present invention has advantages such as high reliability.

[0048] Optionally, the combustion-supporting gas is compressed air.

[0049] In some embodiments, both the first chamber 201 and the second chamber 202 are annular chambers.

[0050] By setting the first chamber 201 and the second chamber 202 as annular chambers, when the combustion-supporting gas enters the second chamber 202 from the intake part 1, it first undergoes annular diffusion and then enters the first chamber 201. The combustion-supporting gas entering the first chamber 201 undergoes annular diffusion again, increasing the flow uniformity of the combustion-supporting gas, which is beneficial to improving the mixing uniformity of the combustion-supporting gas and the fuel, and thus improving the reliability of the test device 100 for detecting the performance of a nozzle of a gas turbine combustion chamber in an embodiment of the present invention.

[0051] In some embodiments, the reverse rectification part 2 includes a first cylinder body 205, a second cylinder body 206, and a first sealing plate 207. The second cylinder body 206 is sleeved outside the first cylinder body 205, and the second cylinder body 206 and the first cylinder body 205 are spaced apart in the inner and outer directions, so that the first cylinder body 205 and the second cylinder body 206 define a second chamber 202. Herein, the inward direction refers to the direction in which the plane perpendicular to the axis of the first cylinder body 205 is adjacent to the axis of the first cylinder body 205, and the outward direction refers to the direction in which the plane perpendicular to the axis of the first cylinder body 205 is away from the axis of the first cylinder body 205. The first cylinder body 205 has a first port 2051 and a second port 2052 that are opposite to each other in its extending direction, and the second cylinder body 206 has a third port 2061 and a fourth port 2062 that are opposite to each other in its extending direction.

[0052] The first sealing plate 207 is annular. The first sealing plate 207 seals the first port 2051. The first sealing plate 207 has a first inner hole 2071 through which at least a part of the nozzle 4 passes, so that the first cylinder body 205 and the nozzle 4 define a first chamber 201, and the first inner hole 2071 forms a nozzle mounting portion 204. Herein, the third port 2061 is arranged closer to the first sealing plate 207 than the fourth port 2062 in the extending direction of the first cylinder body. The first port 2051 and the third port 2061 are arranged staggeredly in the extending direction of the first cylinder body 205, so that the first chamber 201 and the second chamber 202 are connected and communicate with each other.

[0053] To make the technical solution of the present application easier to understand, the technical solution of the present application will be further described below by taking the example that the axis direction of the first cylinder body 205 is consistent with the left - right direction, where the left - right direction is as Figure 1 and Figure 2 shown.

[0054] As Figure 1 and Figure 2 shown, the first port 2051 is located on the left side of the second port 2052, the third port 2061 is located on the left side of the fourth port 2062, and the first sealing plate 207 seals the third port 2061. The first port 2051 and the third port 2061 are spaced apart in the left - right direction. An annular second chamber 202 is formed between the outer peripheral surface of the first cylinder body 205 and the inner peripheral surface of the second cylinder body 206, and an annular first chamber 201 is formed between the inner peripheral surface of the first cylinder body 205 and the outer peripheral surface of the nozzle 4.

[0055] Specifically, the combustion - supporting gas of the intake part 1 enters the annular second chamber 202, flows and diffuses annularly in the annular second chamber 202, and then reversely enters the annular first chamber 201. In the first chamber 201, the combustion - supporting gas further flows and diffuses annularly and then mixes with the fuel ejected from the nozzle orifice 401.

[0056] Thus, an experimental device 100 for detecting the performance of a gas turbine combustion chamber nozzle according to an embodiment of the present invention sets a first cylinder body 205 and a second cylinder body 206, and arranges the second chamber 202 and the first chamber 201 into an annular space. While improving the flow uniformity of the combustion-supporting gas, the experimental device 100 for detecting the performance of a gas turbine combustion chamber nozzle according to an embodiment of the present invention has a simple structure.

[0057] Optionally, the nozzle 4 is fixedly installed on the first sealing plate 207 by a flange.

[0058] For example, the nozzle 4 is provided with a flange, and the first sealing plate 207 is provided with a plurality of blind holes. The flange and the blind holes are connected by bolts, so as to fixedly install the nozzle 4 on the first sealing plate 207.

[0059] In some embodiments, an experimental device 100 for detecting the performance of a gas turbine combustion chamber nozzle further includes a third chamber 203 communicating with the second chamber 202. The third chamber 203 is arranged upstream of the second chamber 202. The third chamber 203 communicates with the intake part 1, and the flow direction of the combustion-supporting gas in the third chamber 203 intersects with the flow direction of the combustion-supporting gas in the second chamber 202.

[0060] The combustion-supporting gas of the intake part 1 enters the annular second chamber 202 through the third chamber 203. Thus, by setting the third chamber 203, it is convenient for the intake part 1 to communicate with the second chamber 202, and further makes the experimental device 100 for detecting the performance of a gas turbine combustion chamber nozzle according to an embodiment of the present invention have a simple structure and convenient connection.

[0061] In some embodiments, the reverse rectifying part 2 further includes a third cylinder body 208, a second sealing plate 209 and a third sealing plate 210. The third cylinder body 208 is sleeved outside the first cylinder body 205. The third cylinder body 208 and the first cylinder body 205 are spaced apart in the inner and outer directions. The inner diameter of the third cylinder body 208 is larger than the inner diameter of the second cylinder body 206. The third cylinder body 208 and the second cylinder body 206 are arranged along the extending direction of the first cylinder body 205. The third cylinder body 208 is arranged upstream of the second cylinder body 206. The third cylinder body 208 has a fifth port 2081 and a sixth port 2082 opposite to each other in its extending direction. The fifth port 2081 is arranged closer to the fourth port 2062 than the sixth port 2082 in the extending direction of the first cylinder body 205.

[0062] Both the second sealing plate 209 and the third sealing plate 210 are annular. The second sealing plate 209 and the third sealing plate 210 are arranged at intervals along the extending direction of the first cylinder 205. The outer end of the second sealing plate 209 is connected to the third cylinder 208, and the inner end of the second sealing plate 209 is connected to the second cylinder 206. The outer end of the third sealing plate 210 is connected to the third cylinder 208, and the inner end of the third sealing plate 210 is connected to the first cylinder 205, so as to define a transition chamber 211 between the third cylinder 208, the first cylinder 205, the second sealing plate 209 and the third sealing plate 210. The transition chamber 211 is arranged downstream of the third chamber 203 and upstream of the second chamber 202.

[0063] For example, as Figure 1 and Figure 2 shown, the third cylinder 208 is arranged on the right side of the second cylinder 206. The fifth port 2081 is located on the left side of the sixth port 2082, and the fifth port 2081 is communicated with the fourth port 2062. The outer peripheral surface of the first cylinder 205, the inner peripheral surface of the third cylinder 208, the right end surface of the second sealing plate 209 and the left end surface of the third sealing plate 210 form an annular transition chamber 211.

[0064] Since the inner diameter of the third cylinder 208 is larger than that of the first cylinder 205, the transition chamber 211 has a larger space in the inner and outer directions, so that the combustion-supporting gas in the third chamber 203 can enter the transition chamber 211 for annular flow diffusion and then enter the second chamber 202, further improving the flow uniformity of the combustion-supporting gas, and thus further being beneficial to improving the reliability of the test device 100 for detecting the performance of the nozzle of a gas turbine combustion chamber according to an embodiment of the present invention.

[0065] Optionally, each of the first cylinder 205, the second cylinder 206 and the third cylinder 208 is coaxially arranged.

[0066] In some embodiments, the reverse rectifying part 2 further includes an annular flow equalizing plate 212. The flow equalizing plate 212 is arranged in the transition chamber 211, and the flow equalizing plate 212 has a plurality of ventilation holes 213 for the combustion-supporting gas to flow through.

[0067] As Figure 1 and Figure 2As shown, the annular flow equalizing plate 212 is sleeved on the first cylinder 205 to divide the transition chamber 211 into an annular first transition chamber and an annular second transition chamber. Among them, the first transition chamber is formed by the outer peripheral surface of the flow equalizing plate 212, the right end surface of the second sealing plate 209, the inner peripheral surface of the third cylinder 208, and the left end surface of the third sealing plate 210. The second transition chamber is formed by the outer peripheral surface of the first cylinder 205 and the inner peripheral surface of the flow equalizing plate 212, so that the combustion supporting gas in the third chamber 203 flows through the first transition chamber in an annular manner and diffuses, and then flows into the second transition chamber through the ventilation holes 213 on the flow equalizing plate 212, thereby further improving the flow uniformity of the combustion supporting gas and further facilitating the improvement of the reliability of the test device 100 for detecting the performance of the combustion chamber nozzle of a gas turbine according to an embodiment of the present invention.

[0068] Optionally, the third cylinder 208 has an opening communicating with the intake part, and the flow equalizing plate 212 is inclined gradually from outside to inside in a direction approaching the first cylinder 205.

[0069] For example, as Figure 1 and Figure 2 shown, the opening on the third cylinder 208 communicates with the third chamber 203, and the combustion supporting gas in the third chamber 203 enters the first transition chamber through the opening on the third cylinder 208. By inclining the flow equalizing plate 212 gradually from outside to inside in a direction approaching the first cylinder 205, the first transition chamber has a larger space relative to the second transition space, which is conducive to the full annular flow and diffusion of the combustion supporting gas entering the first transition chamber, and further conducive to improving the flow uniformity of the combustion supporting gas in the first transition chamber and further facilitating the improvement of the reliability of the test device 100 for detecting the performance of the combustion chamber nozzle of a gas turbine according to an embodiment of the present invention.

[0070] In some embodiments, the outer end of the flow equalizing plate 212 is connected to at least one of the inner end of the second sealing plate 209 or the second cylinder 206, and the inner end of the flow equalizing plate 212 is connected to at least one of the inner end of the third sealing plate 210 and the first cylinder 205.

[0071] For example, as Figure 1 and Figure 2 shown, the outer end of the flow equalizing plate 212 is welded to the second cylinder 206, and the inner end of the flow equalizing plate 212 is welded to the third sealing plate 210, thereby facilitating the installation of the flow equalizing plate 212.

[0072] In some embodiments, the reverse rectifying part 2 further includes a fourth chamber 214, which is arranged upstream of the third chamber 203. The fourth chamber 214 is respectively connected to the third chamber 203 and the intake part 1, and the flow direction of the combustion supporting gas in the fourth chamber 214 intersects with the flow direction of the combustion supporting gas in the third chamber 203.

[0073] As Figure 1 shown, the combustion-supporting gas in the intake part 1 flows from left to right through the combustion-supporting gas in the fourth chamber 214, and the combustion-supporting gas in the third chamber 203 flows from outside to inside into the first transition chamber. By providing the fourth chamber 214, it is further convenient for the combustion-supporting gas in the intake part 1 to enter the first transition chamber.

[0074] Optionally, the reverse rectifying part 2 further includes a fifth chamber 215. The fifth chamber 215 is provided upstream of the fourth chamber 214. The flow direction of the combustion-supporting gas in the fifth chamber 215 intersects with the flow direction of the combustion-supporting gas in the fourth chamber 214. The fifth chamber 215 is respectively connected to the fourth chamber 214 and the intake part 1.

[0075] For example, as Figure 1 shown, the combustion-supporting gas in the intake part 1 enters the fourth chamber 214 through the fifth chamber 215. By providing the fifth chamber 215, it is convenient for the combustion-supporting gas in the intake part 1 to enter the fourth chamber 214, so that the structure of a test device 100 for detecting the performance of a gas turbine combustion chamber nozzle according to an embodiment of the present invention is simple and the layout is reasonable.

[0076] Optionally, the extending direction of the third chamber 203 is perpendicular to the extending direction of the second chamber 202, so that the flow direction of the combustion-supporting gas in the third chamber 203 is perpendicular to the flow direction of the combustion-supporting gas in the second chamber 202.

[0077] Optionally, the extending direction of the fourth chamber 214 is perpendicular to the extending direction of the third chamber 203, so that the flow direction of the combustion-supporting gas in the fourth chamber 214 is perpendicular to the flow direction of the combustion-supporting gas in the third chamber 203.

[0078] Optionally, the extending direction of the fifth chamber 215 is perpendicular to the extending direction of the fourth chamber 214, so that the flow direction of the combustion-supporting gas in the fifth chamber 215 is perpendicular to the flow direction of the combustion-supporting gas in the fourth chamber 214.

[0079] For example, as Figure 1 shown, the combustion-supporting gas in the intake part 1 deflects 90° and enters the fifth chamber 215. The combustion-supporting gas entering the fifth chamber 215 deflects 90° and then enters the fourth chamber 214. The combustion-supporting gas entering the fourth chamber 214 deflects 90° and then enters the third chamber 203. The combustion-supporting gas in the third chamber 203 enters the first transition chamber in a side-inlet manner.

[0080] Thus, by reasonably arranging the first chamber 201, the second chamber 202, the third chamber 203, the fourth chamber 214 and the fifth chamber 215, the structure of a test device 100 for detecting the performance of a gas turbine combustion chamber nozzle according to an embodiment of the present invention is simple and the layout is reasonable.

[0081] In some embodiments, a test device 100 for detecting the performance of a gas turbine combustion chamber nozzle according to an embodiment of the present invention further includes a combustion-supporting gas pipeline 5, which is arranged upstream of the second chamber 202. The combustion-supporting gas pipeline 5 includes a first pipe section 501, a second pipe section 502, and a third pipe section 503 that are connected in sequence. The second pipe section 502 is arranged upstream of the first pipe section 501, and the third pipe section 503 is arranged upstream of the second pipe section 502. The first pipe section 501 defines a third chamber 203, the second pipe section 502 defines a fourth chamber 214, and the third pipe section 503 defines a fifth chamber 215.

[0082] Thus, by forming the third chamber 203, the fourth chamber 214, and the fifth chamber 215 with the first pipe section 501, the second pipe section 502, and the third pipe section 503 of the combustion-supporting gas pipeline 5 respectively, the structure of a test device 100 for detecting the performance of a gas turbine combustion chamber nozzle according to an embodiment of the present invention is simple and convenient for installation.

[0083] Optionally, a plurality of combustion-supporting gas pipelines 5 are provided, and the plurality of combustion-supporting gas pipelines 5 are arranged at intervals along the circumferential direction of the nozzle mounting portion 204.

[0084] As Figure 1 and Figure 3 shown, four combustion-supporting gas pipelines 5 are provided, and the four combustion-supporting gas pipelines 5 are evenly arranged at intervals along the circumferential direction of the nozzle 4 mounting portion 204.

[0085] Thus, the combustion-supporting gas of the intake part 1 enters the transition chamber 211 through multiple combustion-supporting gas pipelines 5, improving the uniformity of the annular flow of the combustion-supporting gas in the transition chamber 211 and further improving the reliability of a test device 100 for detecting the performance of a gas turbine combustion chamber nozzle according to an embodiment of the present invention.

[0086] Optionally, the intake part 1 is an intake pipe, and each combustion-supporting gas pipeline 5 is connected to the intake pipe 1, and the plurality of combustion-supporting gas pipelines 5 are arranged around the center line of the intake pipe.

[0087] By arranging the plurality of combustion-supporting gas pipelines 5 around the center line of the intake pipe, the intake working conditions of each combustion-supporting gas pipeline 5 can be made the same, thereby further improving the reliability of a test device 100 for detecting the performance of a gas turbine combustion chamber nozzle according to an embodiment of the present invention.

[0088] Optionally, the combustion part 3 is a combustion pipe, and at least a part of the combustion pipe extends into the first cylinder 205 so that the first chamber 201 is communicated with the combustion part 3.

[0089] Optionally, the combustion pipe includes a large-diameter section 302 and a small-diameter section 301. The large-diameter section 302 is arranged downstream of the small-diameter section 301, and the small-diameter section 301 extends into the first cylinder 205.

[0090] For example, as Figure 1 shown, the first cylinder body 205 is sleeved on the small-diameter section 301, and the first cylinder body 205 communicates with the small-diameter section 301. The combustion-supporting gas and the fuel ejected from the nozzle orifice 401 are mixed in the small-diameter section 301 and then enter the large-diameter section 302 for combustion. The high-temperature gas generated by the combustion in the large-diameter section 302 is discharged from the right port of the large-diameter section 302.

[0091] Thus, by configuring the combustion part 3 into the small-diameter section 301 and the large-diameter section 302, the structure is simple, which facilitates the combustion of the combustion-supporting gas and the fuel mixed in the first cylinder body 205 in the combustion part.

[0092] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus cannot be understood as a limitation to the present invention.

[0093] In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one of such features. In the description of the present invention, the meaning of "a plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0094] In the present invention, unless otherwise clearly specified and limited, the terms "mounted", "connected", "connected to", "fixed", etc. should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or integrated; it may be a mechanical connection, an electrical connection, or communicable with each other; it may be directly connected, or indirectly connected through an intermediate medium, and may be the internal communication of two elements or the interaction relationship between two elements, unless otherwise clearly limited. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0095] In the present invention, unless otherwise clearly specified or limited, a first feature being "on" or "under" a second feature may mean that the first and second features are in direct contact, or the first and second features are indirectly in contact via an intermediate medium. Further, a first feature being "above", "over" and "on top of" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the horizontal height of the first feature is higher than that of the second feature. A first feature being "under", "below" and "beneath" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the horizontal height of the first feature is less than that of the second feature.

[0096] In the present invention, the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples", etc. mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, without contradiction, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples.

[0097] Although the above embodiments have been shown and described, it is to be understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions, and variations made by those of ordinary skill in the art to the above embodiments are within the scope of the present invention.

Claims

1. An experimental device for detecting the performance of the nozzle of a gas turbine combustion chamber, characterized in that, Comprising: An intake part for allowing the combustion-supporting gas to enter; A reverse rectifying part, which includes a first chamber, a second chamber and a nozzle mounting part. The first chamber is arranged downstream of the second chamber, the first chamber communicates with the second chamber, the second chamber communicates with the intake part, the flow direction of the combustion-supporting gas in the first chamber is opposite to that in the second chamber, and the nozzle mounting part is used for mounting a nozzle through which fuel flows; And A combustion part, which communicates with the first chamber and is used to communicate with the nozzle so that the combustion-supporting gas and the fuel are mixed and burned to form high-temperature gas; The reverse rectifying part includes: A first cylinder and a second cylinder. The second cylinder is sleeved outside the first cylinder, and the second cylinder and the first cylinder are spaced apart in the inner and outer directions so that the first cylinder and the second cylinder define the second chamber. The first cylinder has a first port and a second port opposite to each other in its extending direction, and the second cylinder has a third port and a fourth port opposite to each other in its extending direction; and An annular first sealing plate that seals the first port. The first sealing plate has a first inner hole through which at least a part of the nozzle passes, so that the first cylinder and the nozzle define the first chamber; Wherein, the third port is arranged closer to the first sealing plate than the fourth port in the extending direction of the first cylinder, and the first port and the third port are arranged staggeredly in the extending direction of the first cylinder so that the first chamber and the second chamber are connected.

2. The test device for detecting the performance of the nozzle of a gas turbine combustion chamber according to claim 1, characterized in that, Both the first chamber and the second chamber are annular chambers.

3. The test device for detecting the performance of the nozzle of a gas turbine combustor according to claim 2, characterized in that, It further includes a third chamber communicating with the second chamber. The third chamber is arranged upstream of the second chamber, the third chamber communicates with the intake part, and the flow direction of the combustion-supporting gas in the third chamber intersects with that in the second chamber.

4. The test device for detecting the performance of the nozzle of a gas turbine combustor according to claim 3, characterized in that, The reverse rectifying part further includes: A third cylinder, which is sleeved outside the first cylinder. The third cylinder and the first cylinder are spaced apart in the inner and outer directions. The inner diameter of the third cylinder is larger than that of the second cylinder. The third cylinder and the second cylinder are arranged along the extending direction of the first cylinder. The third cylinder is arranged upstream of the second cylinder. The third cylinder has a fifth port and a sixth port opposite to each other in its extending direction. The fifth port is arranged closer to the fourth port than the sixth port in the extending direction of the first cylinder; and An annular second sealing plate and an annular third sealing plate, the second sealing plate and the third sealing plate are arranged at intervals along the extending direction of the first cylinder body, the outer end of the second sealing plate is connected to the third cylinder body, the inner end of the second sealing plate is connected to the second cylinder body, the outer end of the third sealing plate is connected to the third cylinder body, and the inner end of the third sealing plate is connected to the first cylinder body, so as to define a transition chamber between the third cylinder body, the first cylinder body, the second sealing plate and the third sealing plate. The transition chamber is arranged downstream of the third chamber and upstream of the second chamber.

5. The test device for detecting the performance of the nozzle of a gas turbine combustor according to claim 4, characterized in that, The reverse rectifying part further includes an annular flow equalizing plate, the flow equalizing plate is arranged in the transition chamber, and the flow equalizing plate is provided with a plurality of ventilation holes for the combustion-supporting gas to flow through.

6. The test device for detecting the performance of the nozzle of a gas turbine combustion chamber according to claim 5, characterized in that, The third cylinder body has an opening communicated with the intake part, and the flow equalizing plate is inclined gradually from outside to inside towards the direction close to the first cylinder body.

7. The test device for detecting the performance of the nozzle of a gas turbine combustor according to claim 6, characterized in that, The outer end of the flow equalizing plate is connected to at least one of the inner end of the second sealing plate or the second cylinder body, and the inner end of the flow equalizing plate is connected to at least one of the inner end of the third sealing plate and the first cylinder body.

8. A test device for detecting the performance of a gas turbine combustion chamber nozzle according to any one of claims 3-7, characterized in that, The reverse rectifying part further includes a fourth chamber, the fourth chamber is arranged upstream of the third chamber, the fourth chamber is respectively communicated with the third chamber and the intake part, and the flow direction of the combustion-supporting gas in the fourth chamber intersects with the flow direction of the combustion-supporting gas in the third chamber.

9. The test device for detecting the performance of the nozzle of a gas turbine combustor according to claim 8, characterized in that The reverse rectifying part further includes a fifth chamber, the fifth chamber is arranged upstream of the fourth chamber, the flow direction of the combustion-supporting gas in the fifth chamber intersects with the flow direction of the combustion-supporting gas in the fourth chamber, and the fifth chamber is respectively communicated with the fourth chamber and the intake part.

10. A test device for detecting the performance of a gas turbine combustion chamber nozzle according to claim 9, characterized in that, The extending direction of the third chamber is perpendicular to the extending direction of the second chamber, so that the flow direction of the combustion-supporting gas in the third chamber is perpendicular to the flow direction of the combustion-supporting gas in the second chamber; and / or The extending direction of the fourth chamber is perpendicular to the extending direction of the third chamber, so that the flow direction of the combustion-supporting gas in the fourth chamber is perpendicular to the flow direction of the combustion-supporting gas in the third chamber; and / or The extending direction of the fifth chamber is perpendicular to the extending direction of the fourth chamber, so that the flow direction of the combustion-supporting gas in the fifth chamber is perpendicular to the flow direction of the combustion-supporting gas in the fourth chamber.

11. The test device for detecting the performance of the nozzle of a gas turbine combustor according to claim 9, characterized in that, It further includes a combustion-supporting gas pipeline, the combustion-supporting gas pipeline is arranged upstream of the second chamber, the combustion-supporting gas pipeline includes a first pipe section, a second pipe section and a third pipe section which are connected in sequence, the second pipe section is arranged upstream of the first pipe section, the third pipe section is arranged upstream of the second pipe section, the first pipe section defines the third chamber, the second pipe section defines the fourth chamber, and the third pipe section defines the fifth chamber.

12. The test device for detecting the performance of the nozzle of a gas turbine combustion chamber according to claim 11, characterized in that, A plurality of the combustion-supporting gas pipelines are provided, and the plurality of combustion-supporting gas pipelines are arranged at intervals along the circumferential direction of the nozzle mounting part.

13. A test device for detecting the performance of a gas turbine combustion chamber nozzle according to claim 12, wherein the air intake part is an intake pipe, each of the combustion-supporting gas pipelines is communicated with the intake pipe, and a plurality of the combustion-supporting gas pipelines are arranged around the central axis of the intake pipe.

14. A test device for detecting the performance of a gas turbine combustion chamber nozzle according to any one of claims 2-7, wherein the combustion part is a combustion pipe, and at least a part of the combustion pipe extends into the first cylinder body so that the first chamber is communicated with the combustion part.

15. A test device for detecting the performance of a gas turbine combustion chamber nozzle according to claim 14, wherein the combustion pipe comprises a large-diameter section and a small-diameter section, the large-diameter section is arranged downstream of the small-diameter section, and the small-diameter section extends into the first cylinder body.

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