CN112595520A - Gas compressor test bench and test method - Google Patents

Gas compressor test bench and test method Download PDF

Info

Publication number
CN112595520A
CN112595520A CN201910870404.9A CN201910870404A CN112595520A CN 112595520 A CN112595520 A CN 112595520A CN 201910870404 A CN201910870404 A CN 201910870404A CN 112595520 A CN112595520 A CN 112595520A
Authority
CN
China
Prior art keywords
compressor
fluid
heat transfer
casing
wall
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN201910870404.9A
Other languages
Chinese (zh)
Inventor
高国荣
曾瑞慧
闫转运
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
AECC Commercial Aircraft Engine Co Ltd
Original Assignee
AECC Commercial Aircraft Engine Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by AECC Commercial Aircraft Engine Co Ltd filed Critical AECC Commercial Aircraft Engine Co Ltd
Priority to CN201910870404.9A priority Critical patent/CN112595520A/en
Publication of CN112595520A publication Critical patent/CN112595520A/en
Pending legal-status Critical Current

Links

Images

Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00—Testing of engines
    • G01M15/14—Testing gas-turbine engines or jet-propulsion engines
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M13/00—Testing of machine parts
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00—Testing of engines
    • G01M15/02—Details or accessories of testing apparatus

Landscapes

  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Positive-Displacement Pumps (AREA)

Abstract

The invention relates to a gas compressor test bed and a gas compressor test method, wherein the test bed comprises a shell, the inner wall of the shell and the outer wall of a casing of the gas compressor form a heat transfer fluid channel by a radial gap between the inner wall of the shell and the outer wall of the casing of the gas compressor, and the heat transfer fluid channel is provided with an inlet part for receiving fluid and an outlet part for discharging the fluid; a fluid delivery control system for controlling fluid input into the inlet portion into the heat transfer fluid channel; in the test state of the compressor test bed, the fluid transmission control system starts fluid transmission to the inlet part and the outlet part of the heat transfer fluid channel, so that fluid flows in the fluid channel and is subjected to heat transmission with the outer wall of the compressor casing to adjust the thermal expansion amount of the compressor casing in the test state, and the blade tip clearance of the compressor rotor in the test state is adjusted. The test bench and the test method have the advantages of simple structure, high test efficiency and the like.

Description

Gas compressor test bench and test method
Technical Field
The invention relates to a gas compressor test bed and a test method.
Background
The test verification of the aero-engine compressor performance test piece is an essential step in the aero-engine design process, and the design and the test of the blade tip clearance are of great importance in the performance test process of the aero-engine compressor test piece.
In the test process, the change of the blade tip clearance is usually formed by the coupling of factors such as the centrifugal force action of the blades, the thermal expansion of a wheel disc and the thermal expansion of a casing, the influence factors are numerous and are difficult to accurately simulate and calculate, and the following two conditions are often caused:
1. the clearance of the rotor blade tips of the actual test piece is small, for safety consideration, the rotor blade tips have to be disassembled on the next stage for scraping and grinding, and then the rotor blade tips are tested on the previous stage again, so that the whole process of the reinstallation on the next stage consumes manpower, material resources and time;
2. if the rotor tip clearance is too large, the performance of the test piece may be too poor and far from the design target, which may cause inaccurate and unusable test results and even the compressor test piece may have to be scrapped.
It can be known from the above that, in the field of compressor testing, in the prior art, generally, an adjustment means of disassembly-rotor blade tip scraping-reinstallation is adopted for testing the blade tip clearance of the compressor, and repeated disassembly-installation steps will result in low testing efficiency, and the blade tip scraping amount may have processing errors, which may result in errors of the test result.
Therefore, a simpler, efficient and accurate compressor testing method and a compressor testing bench are needed in the art.
Disclosure of Invention
One object of the present invention is to provide a compressor test rig.
Another object of the present invention is to provide a compressor testing method.
According to one aspect of the invention, a compressor test rig comprises: the heat transfer fluid channel is provided with an inlet part for receiving fluid and an outlet part for discharging the fluid; a fluid delivery control system for controlling fluid input into the inlet portion into the heat transfer fluid channel; in the test state of the compressor test bed, the fluid transmission control system starts fluid transmission to the inlet part of the heat transfer fluid channel, so that fluid flows in the heat transfer fluid channel and is subjected to heat transfer with the outer wall of the compressor casing to adjust the thermal expansion amount of the compressor casing in the test state, and the blade tip clearance of the compressor rotor in the test state is adjusted.
In one or more embodiments of the compressor test rig, the inlet portion includes a main inlet at one side end of the fluid passage, and the outlet portion includes a main outlet at the other side end of the fluid passage, the main inlet communicating with the main outlet.
In one or more embodiments of the compressor test rig, the heat transfer fluid channel includes a plurality of heat transfer fluid channel segments corresponding to a plurality of rotor tip clearances of the compressor, at least one of the heat transfer fluid channel segments is a partial channel, and a flow control valve is provided to control fluid input and output to the partial channel, so as to adjust thermal expansion of a casing of the compressor at a corresponding position of the partial channel, and thus adjust the rotor tip clearance at a corresponding position.
In one or more embodiments of the compressor test rig, the inlet portion of the heat transfer fluid passage includes an inlet orifice in a shell side wall of the partial passage and the outlet portion includes an outlet orifice in the shell side wall of the partial passage.
In one or more embodiments of the compressor test rig, the inlet holes and the outlet holes are axially positioned and circumferentially staggered.
In one or more embodiments of the compressor test rig, the fluid delivery control system includes a fluid circulation device that causes fluid discharged from the outlet portion to pass through the circulation device before being output to the inlet portion, and a heat exchange device that controls a temperature of the fluid output to the inlet portion.
In one or more embodiments of the compressor test rig, the fluid of any of the above is air
According to another aspect of the invention, a method for testing a compressor includes measuring a target rotor tip clearance of the compressor, including:
s1: measuring a current rotor tip clearance (C) of the compressor and a corresponding current compressor performance parameter (P);
s2: applying a wrapping piece to a compressor casing, forming a wrapping cavity by the inner wall surface of the wrapping piece and the outer wall surface of the compressor casing, and inputting heat transfer fluid into the wrapping cavity, so that the thermal expansion amount of the compressor casing is adjusted by the heat transfer action on the outer wall of the compressor casing, the current rotor gap is adjusted to the tip gap of the other rotor, and the performance parameter of the compressor corresponding to the tip gap of the other rotor is measured;
s3: and repeating S1 and S2, measuring to obtain a group of compressor performance parameters (P0, P1, P2, … … and Pn) corresponding to the blade tip clearances (C0, C1, C2, … … and Cn), and obtaining the target rotor blade tip clearance of the compressor according to the performance parameters of the compressor.
In one or more embodiments of the compressor testing method, the step of adjusting the thermal expansion amount of the compressor casing through the heat transfer effect on the outer wall of the compressor casing comprises the following specific steps:
a housing is provided along with a fluid delivery control system,
the shell is arranged to surround the casing at the radial outer part of the compressor casing, the inner wall of the shell and the outer wall of the compressor casing form a heat transfer fluid channel by a radial clearance between the inner wall of the shell and the outer wall of the compressor casing,
providing the fluid delivery control system to control fluid input to the heat transfer fluid channel;
when the current rotor blade tip clearance needs to be adjusted, the fluid transmission control system starts fluid input to the heat transfer fluid channel, so that fluid enters the heat transfer fluid channel to be subjected to heat transfer with the outer wall of the compressor casing, the thermal expansion amount of the compressor casing is adjusted, and the current compressor rotor blade tip clearance is adjusted.
In one or more embodiments of the compressor testing method, the specific step of adjusting the thermal expansion amount of the compressor casing through the heat transfer effect on the outer wall of the compressor casing comprises the following steps:
the fluid flows through the outer wall of the compressor casing, and the thermal expansion amount of the compressor casing is adjusted through the action of the fluid and a transmission body of the outer wall of the compressor casing.
In one or more embodiments of the compressor testing method, the region where the fluid flows through the outer wall of the compressor casing includes the entire outer wall of the compressor casing, or the outer wall region of the casing corresponding to one or more stages of the compressor.
The advanced effects of the invention include one or a combination of the following:
1. in the test process of the gas compressor, the wrapping piece is applied to the outer part of the casing, the thermal expansion amount of the casing is adjusted by actively inputting heat transfer fluid, the instant online control of the blade tip clearance of the gas compressor is realized, and the defects that the blade tip clearance is required to be scraped and ground in the prior art, the test efficiency in the process of halt, disassembly and installation is low and the like are overcome;
2. the gas compressor test bed adopts a double-layer structure that a shell is arranged outside a casing, and a heat transfer fluid channel is constructed by utilizing the gap between the casing and the shell, so that the structure is simple and compact; meanwhile, a control circuit and a sensor mounting site can be arranged on the shell, so that the structure compactness and the measurement accuracy are further improved;
3. the gas compressor test bed adopts a double-layer structure that a shell is arranged outside a casing, so that the test safety can be improved, and the damage of a gas compressor test piece to the test bed due to surging accidents and other events can be avoided.
Drawings
The above and other features, nature, and advantages of the present invention will become more apparent from the following description of the embodiments taken in conjunction with the accompanying drawings in which like reference characters refer to like features throughout, it being noted that the drawings are given by way of example only and are not to scale, and should not be taken as limiting the scope of the invention which is actually claimed, wherein:
FIG. 1 is a schematic illustration of a shell-to-case configuration of a compressor test rig in accordance with an embodiment;
FIG. 2 is a schematic illustration of a shell-to-casing configuration of a compressor test rig according to another embodiment;
fig. 3 is a schematic structural diagram of an inlet and an outlet of a test stand of a compressor according to an embodiment.
Detailed Description
The present invention is further described in the following description with reference to specific embodiments and the accompanying drawings, wherein the details are set forth in order to provide a thorough understanding of the present invention, but it is apparent that the present invention can be embodied in many other forms different from those described herein, and it will be readily appreciated by those skilled in the art that the present invention can be implemented in many different forms without departing from the spirit and scope of the invention.
It is to be understood that the directional terms such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal" and "top, bottom" and the like are generally used herein based on the orientation or positional relationship shown in the drawings for convenience in describing the present invention and simplicity in description, and are not intended to limit the scope of the present invention since the directional terms are not used to indicate and imply that the referenced apparatus or component must have a particular orientation or be constructed and operated in a particular orientation. Also, this application uses specific language to describe embodiments of the application. Reference throughout this specification to "one embodiment," "an embodiment," and/or "some embodiments" means that a particular feature, structure, or characteristic described in connection with at least one embodiment of the present application is included in at least one embodiment of the present application. Therefore, it is emphasized and should be appreciated that two or more references to "an embodiment" or "one embodiment" or "an alternative embodiment" in various places throughout this specification are not necessarily all referring to the same embodiment. Furthermore, some features, structures, or characteristics of one or more embodiments of the present application may be combined as appropriate.
As shown in fig. 1, in one embodiment, a compressor test rig 100 includes a housing 1, a fluid delivery control system 2. The compressor 10 includes a casing 3, a stator blade 4, and a rotor blade 5, and a radial gap between a tip of the rotor blade 5 and an inner wall of the casing 3 forms a tip gap 6. The casing 1 is used for surrounding a casing 3 of a compressor 10 at the radial outer part of the casing 3, the inner wall of the casing 1 and the outer wall of the casing 3 form a heat transfer fluid channel 7 with a radial gap therebetween, and the heat transfer fluid channel 7 is provided with an inlet part 8 for receiving fluid and an outlet part 9 for discharging fluid. The fluid transmission control system 2 is used for controlling the fluid input into the inlet portion 8 into the heat transfer fluid channel 7, and specifically, the control manner may be to control the flow rate, temperature, fluid type, and the like of the fluid. With continued reference to fig. 1, in an embodiment, the fluid transfer control system 2 may include a fluid circulation device 21 and a heat exchange device 22, the fluid circulation device 21 may output the fluid discharged from the outlet portion 9 to the inlet portion 8 after passing through the fluid circulation device 21, so that the gas is circulated and utilized, the heat exchange device 22 may control the temperature of the fluid output to the inlet portion 8 through a heat exchange effect, the heat exchange device 22 may be a heat exchanger, and the fluid circulation device 21 may be a pump, but is not limited thereto.
In a test state of the compressor test bed 100, the fluid transmission control system 2 starts fluid transmission to the inlet portion 8 of the heat transfer fluid channel 7, so that fluid flows in the heat transfer fluid channel 7 and is in heat transfer with the outer wall of the casing 3 of the compressor 10, the thermal expansion amount of the casing 3 of the compressor 10 in the test state is adjusted, and the blade tip clearance 6 of the compressor rotor in the test state is adjusted.
For example, during testing, when it was desired to increase the tip clearance 6, the temperature of the high temperature fluid supplied or the temperature of the supplied fluid was increased to the inlet portion 8 of the heat transfer fluid channel 7, which transferred heat to the outer wall of the casing 3, increasing the temperature of the casing 3, increasing the casing thermal expansion, and thus increasing the rotor tip clearance 6.
The gas compressor test bed has the advantages that the shell and the fluid transmission control system are arranged, so that the thermal expansion amount of the casing is adjusted by actively inputting the heat transfer fluid, the instant online control on the blade tip clearance of the gas compressor is realized, the gas compressor test efficiency is improved, meanwhile, the double-layer structure of the shell is arranged outside the casing, the heat transfer fluid channel is constructed by utilizing the clearance between the casing and the heat transfer fluid channel, and the structure is simple and compact; meanwhile, a control circuit and a sensor mounting site can be arranged on the shell, so that the structure compactness and the measurement accuracy are further improved; and the test bench adopts a double-layer structure that the casing is arranged outside the casing, so that the test safety can be improved, and the damage of the gas compressor test piece to the test bench due to surging accidents and other events can be avoided.
Referring to fig. 2, in an embodiment, a specific structure of the heat transfer fluid channel 7 may be exemplified in that the inlet portion 8 includes a main inlet 81 at one side end of the fluid channel, the outlet portion 9 includes a main outlet 91 at the other side end of the fluid channel 7, and the main inlet 81 is communicated with the main outlet 91, so that when gas is introduced into the heat transfer fluid channel 7, since the main inlet 81 is communicated with the main outlet 91, it is possible to control each rotor tip clearance 6 corresponding to each rotor blade 5 of the casing 3 to be increased in real time, so that the casing 3 is expanded as a whole, and the rotor tip clearance is increased as a whole.
Referring to fig. 1, in an embodiment, the specific structure of the heat transfer fluid channel 7 may also be exemplified by that the heat transfer fluid channel 7 includes a plurality of heat transfer fluid channel segments corresponding to a plurality of rotor tip clearances of the compressor, for example, the heat transfer fluid channel segment 71 corresponding to the rotor tip clearance 61 shown in fig. 1 and the heat transfer fluid channel segment 72 corresponding to the rotor tip clearance 62. At least one of the plurality of heat transfer fluid passage sections is a partial passage provided with a flow control valve, for example, as shown in fig. 1, the heat transfer fluid passage section 71 is a partial passage provided with flow control valves 711 and 712 to control fluid input and output to the partial passage, respectively, the heat transfer fluid passage section 72 is a partial passage provided with flow valves 713 and 714 to control fluid input and output to the partial passage, respectively, to adjust the thermal expansion amount of the casing of the stage of the compressor corresponding to the partial passage, thereby adjusting the rotor tip clearance of the stage. The beneficial effect of such an arrangement is that control of the increase or decrease in rotor tip clearance for a particular stage of the compressor can be achieved in practical tests.
Referring to fig. 3, in an embodiment, an example of a specific structure having an inlet portion and an outlet portion corresponding to a plurality of heat transfer fluid channel segments may be that the inlet portion 8 of the heat transfer fluid channel 7 includes inflow holes, such as 4 inflow holes 82, 83, 84, 85 shown in fig. 3, located in the side wall of the housing 1 of the partial channel, and the outlet portion 9 includes outflow holes, such as 4 outflow holes 92, 93, 94, 95 shown in fig. 3, located in the side wall of the housing 1 of the partial channel, which makes it easier to control the flow rate of the inflow air and the outflow air in the partial channel. Further, as shown in fig. 3, the axial positions of the inflow holes 82, 83, 84, 85 and the outflow holes 92, 93, 94, 95 are the same, and the inflow holes and the outflow holes are staggered in the circumferential direction, so that the flow effect in the partial passage can be further optimized, and the heat transfer effect on the casing 3 can be enhanced.
As can be seen from the embodiments of fig. 2 and 1, the heat transfer action between the fluid in the heat transfer fluid channel and the casing may be a heat transfer action between the fluid and the entire outer wall of the casing 3, so as to adjust the thermal expansion amount of the entire casing 3, thereby adjusting the entire tip clearance. Or the heat transfer action is generated in the outer wall area of the casing 3 corresponding to the specific stage or stages of the compressor, and the local expansion amount of the casing is adjusted, so that the local blade tip clearance is adjusted, and the target blade tip clearance of the specific stage or stages of the compressor is measured and obtained.
From the above description, in the test of the compressor, in order to measure the optimal rotor tip clearance under a certain performance parameter of the compressor, i.e. the target rotor tip clearance, the steps may include,
s1: measuring a current rotor tip clearance (C) of the compressor and a corresponding current compressor performance parameter (P);
s2: applying a wrapping member to a compressor casing, for example, the wrapping member applied to the casing 3 shown in fig. 1 to 3 is a casing 1, forming a wrapping cavity by an inner wall surface of the wrapping member and an outer wall surface of the compressor casing, for example, a heat transfer fluid channel 7 is formed by a radial gap between an inner wall of the casing 1 shown in fig. 1 to 3 and an outer wall of the compressor casing 3, inputting the heat transfer fluid into the wrapping cavity, so that the thermal expansion amount of the compressor casing is adjusted by the heat transfer action on the outer wall of the compressor casing, the current rotor gap is adjusted to another rotor tip gap, and the compressor performance parameter corresponding to the another rotor tip gap is measured. For example, the fluid delivery control system 2 shown in fig. 1 is configured to control fluid input to the heat transfer fluid channel 7, and when it is desired to adjust the current rotor tip clearance, the fluid delivery control system 2 opens fluid input to the heat transfer fluid channel 7. For example, when the rotor blade tip clearance needs to be increased, high-temperature fluid is filled into the coating cavity to heat the casing 3 or reduce the heat dissipation of the casing 3, so that the temperature of the casing is increased, the thermal expansion of the casing is increased, and the rotor blade tip clearance 6 is increased; when the rotor tip clearance needs to be reduced, for example, cold air is filled into the coating cavity to cool the casing 3, so that the thermal expansion of the casing 3 is reduced, and the rotor tip clearance 6 is further reduced. The performance parameters of the air compressor can be air flow, compression ratio, compression efficiency and the like, and are selected according to specific test requirements.
S3: repeating S1 and S2 to obtain a group of rotor blade tip clearances (C)0，C1，C2，……，Cn) Corresponding compressor performance parameter (P)0，P1，P2，……，Pn) And obtaining the target rotor tip clearance of the compressor according to the performance parameters of the compressor. For example, different compression ratios corresponding to different tip clearances are measured, and if a high compression ratio is desired, the rotor tip clearance corresponding to the highest compression ratio is the target rotor tip clearance. It will be appreciated that other performance parameters may be used for the corresponding rotor tip clearances, and that the above-described example of compression ratios is not intended to be limiting.
In summary, the advantages of the compressor test bench and the test method adopting the above embodiments include one or a combination of the following:
1. in the test process of the gas compressor, the wrapping piece is applied to the outer part of the casing, the thermal expansion amount of the casing is adjusted by actively inputting heat transfer fluid, the instant online control of the blade tip clearance of the gas compressor is realized, and the defects that the blade tip clearance is required to be scraped and ground in the prior art, the test efficiency in the process of halt, disassembly and installation is low and the like are overcome;
2. the gas compressor test bed adopts a double-layer structure that a shell is arranged outside a casing, and a heat transfer fluid channel is constructed by utilizing the gap between the casing and the shell, so that the structure is simple and compact; meanwhile, a control circuit and a sensor mounting site can be arranged on the shell, so that the structure compactness and the measurement accuracy are further improved;
3. the gas compressor test bed adopts a double-layer structure that a shell is arranged outside a casing, so that the test safety can be improved, and the damage of a gas compressor test piece to the test bed due to surging accidents and other events can be avoided.
Although the above examples describe specific embodiments of the present invention, it will be appreciated by those skilled in the art that these are by way of illustration only, and that the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the invention, and these changes and modifications are within the scope of the invention.

Claims (11)

1. A gas compressor test bench is characterized by comprising
The heat transfer fluid channel is provided with an inlet part for receiving fluid and an outlet part for discharging the fluid;
a fluid delivery control system for controlling fluid input into the inlet portion into the heat transfer fluid channel;
in the test state of the compressor test bed, the fluid transmission control system starts fluid transmission to the inlet part of the heat transfer fluid channel, so that fluid flows in the heat transfer fluid channel and is subjected to heat transfer with the outer wall of the compressor casing to adjust the thermal expansion amount of the compressor casing in the test state, and the blade tip clearance of the compressor rotor in the test state is adjusted.
2. The test rig according to claim 1, wherein the inlet portion comprises a main inlet at one side end of the fluid passage and the outlet portion comprises a main outlet at the other side end of the fluid passage, the main inlet communicating with the main outlet.
3. The test rig according to claim 1, wherein the heat transfer fluid channel includes a plurality of heat transfer fluid channel segments disposed in correspondence with a plurality of rotor tip clearances of the compressor, at least one of the plurality of heat transfer fluid channel segments being a partial channel provided with a flow control valve to control fluid input and output to the partial channel to adjust an amount of thermal expansion of a casing of the compressor at a corresponding location of the partial channel to adjust the rotor tip clearance at the corresponding location.
4. The test rig of claim 3, wherein the inlet portion of the heat transfer fluid channel includes an inlet orifice in the housing sidewall of the partial channel and the outlet portion includes an outlet orifice in the housing sidewall of the partial channel.
5. The test rig of claim 4, wherein the inlet holes are axially co-located with the outlet holes and are circumferentially staggered.
6. The test rig according to claim 1, wherein the fluid delivery control system includes a fluid circulation device that causes fluid discharged from the outlet portion to pass through the circulation device and be output to the inlet portion, and a heat exchange device that controls a temperature of the fluid output to the inlet portion.
7. The test rig according to any of claims 1-6, wherein the fluid is air.
8. A test method of a compressor comprises the steps of measuring a target rotor tip clearance of the compressor, and is characterized by comprising the following steps:
s1: measuring a current rotor tip clearance (C) of the compressor and a corresponding current compressor performance parameter (P);
s2: applying a wrapping piece to a compressor casing, forming a wrapping cavity by the inner wall surface of the wrapping piece and the outer wall surface of the compressor casing, and inputting heat transfer fluid into the wrapping cavity, so that the thermal expansion amount of the compressor casing is adjusted by the heat transfer action on the outer wall of the compressor casing, the current rotor gap is adjusted to the tip gap of the other rotor, and the performance parameter of the compressor corresponding to the tip gap of the other rotor is measured;
s3: repeating S1 and S2 to obtain a group of blade tip clearances (C)0，C1，C2，……，Cn) Corresponding compressor performance parameter (P)0，P1，P2，……，Pn) And obtaining the target rotor tip clearance of the compressor according to the performance parameters of the compressor.
9. The test method of claim 8, wherein the step of adjusting the amount of thermal expansion of the compressor casing by heat transfer to the outer wall of the compressor casing comprises:
a housing is provided along with a fluid delivery control system,
the shell is arranged to surround the casing at the radial outer part of the compressor casing, the inner wall of the shell and the outer wall of the compressor casing form a heat transfer fluid channel by a radial clearance between the inner wall of the shell and the outer wall of the compressor casing,
providing the fluid delivery control system to control fluid input to the heat transfer fluid channel;
when the current rotor blade tip clearance needs to be adjusted, the fluid transmission control system starts fluid input to the heat transfer fluid channel, so that fluid enters the heat transfer fluid channel to be subjected to heat transfer with the outer wall of the compressor casing, the thermal expansion amount of the compressor casing is adjusted, and the current compressor rotor blade tip clearance is adjusted.
10. The test method of claim 8, wherein the step of adjusting the amount of thermal expansion of the compressor casing by heat transfer to the outer wall of the compressor casing comprises:
the fluid flows through the outer wall of the compressor casing, and the thermal expansion amount of the compressor casing is adjusted through the action of the fluid and a transmission body of the outer wall of the compressor casing.
11. The test method of claim 10, wherein the region where the fluid flows through the outer wall of the compressor case comprises an integral outer wall of the compressor case or an outer wall region of the case corresponding to one or more stages of the compressor.
CN201910870404.9A 2019-09-16 2019-09-16 Gas compressor test bench and test method Pending CN112595520A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201910870404.9A CN112595520A (en) 2019-09-16 2019-09-16 Gas compressor test bench and test method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201910870404.9A CN112595520A (en) 2019-09-16 2019-09-16 Gas compressor test bench and test method

Publications (1)

Publication Number Publication Date
CN112595520A true CN112595520A (en) 2021-04-02

Family

ID=75180037

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201910870404.9A Pending CN112595520A (en) 2019-09-16 2019-09-16 Gas compressor test bench and test method

Country Status (1)

Country Link
CN (1) CN112595520A (en)

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2003166500A (en) * 2001-11-30 2003-06-13 Ishikawajima Harima Heavy Ind Co Ltd Method for and structure of adjusting gap between blade tips of gas turbine
JP2010248994A (en) * 2009-04-15 2010-11-04 Panasonic Corp Scroll compressor and assembling method of the same
US20120167588A1 (en) * 2010-12-30 2012-07-05 Douglas David Dierksmeier Compressor tip clearance control and gas turbine engine
CN103089339A (en) * 2011-10-31 2013-05-08 通用电气公司 Active clearance control system and method for gas turbine engine
CN103775139A (en) * 2012-10-26 2014-05-07 中航商用航空发动机有限责任公司 Gap control system and method for turbine engine
US20160097296A1 (en) * 2014-10-06 2016-04-07 General Electric Comapny System and method for blade tip clearance control
CN107435563A (en) * 2017-05-05 2017-12-05 西北工业大学 A kind of case structure with tip clearance control and the flowing control of leaf top
EP3489466A1 (en) * 2017-11-24 2019-05-29 Ansaldo Energia Switzerland AG Gas turbine assembly

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2003166500A (en) * 2001-11-30 2003-06-13 Ishikawajima Harima Heavy Ind Co Ltd Method for and structure of adjusting gap between blade tips of gas turbine
JP2010248994A (en) * 2009-04-15 2010-11-04 Panasonic Corp Scroll compressor and assembling method of the same
US20120167588A1 (en) * 2010-12-30 2012-07-05 Douglas David Dierksmeier Compressor tip clearance control and gas turbine engine
CN103089339A (en) * 2011-10-31 2013-05-08 通用电气公司 Active clearance control system and method for gas turbine engine
CN103775139A (en) * 2012-10-26 2014-05-07 中航商用航空发动机有限责任公司 Gap control system and method for turbine engine
US20160097296A1 (en) * 2014-10-06 2016-04-07 General Electric Comapny System and method for blade tip clearance control
CN107435563A (en) * 2017-05-05 2017-12-05 西北工业大学 A kind of case structure with tip clearance control and the flowing control of leaf top
EP3489466A1 (en) * 2017-11-24 2019-05-29 Ansaldo Energia Switzerland AG Gas turbine assembly

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
王子登，王永明，黄国平: "压气机转子叶尖间隙对其性能的影响", 《燃气涡轮试验与研究》 *

Similar Documents

Publication Publication Date Title
Eckardt Instantaneous measurements in the jet-wake discharge flow of a centrifugal compressor impeller
Barringer et al. The design of a steady aero thermal research turbine (START) for studying secondary flow leakages and airfoil heat transfer
JP5825811B2 (en) Method, system, and apparatus for calculating tip clearance in turbine engine
CA2455280A1 (en) Method and apparatus for monitoring the performance of a gas turbine system
US9188504B2 (en) Methods for testing turbine blades
Chana et al. The design, development and testing of a non-uniform inlet temperature generator for the QinetiQ transient turbine research facility
CN103775139A (en) Gap control system and method for turbine engine
CN104359679A (en) Method for measuring micropore flow coefficient under rotating condition
Guidotti et al. Experimental and numerical analysis of the flow field in the impeller of a centrifugal compressor stage at design point
CN113357014A (en) Method for fuel delivery
RU2562361C1 (en) Cooling method of turbine work blade of gas-turbine engine
CN114235319A (en) Hollow turbine blade testing device and method
CN112595520A (en) Gas compressor test bench and test method
CN109443782A (en) A kind of device of the air-cooled turbine guide vane cooling air stream measurement of aero-engine
Aalburg et al. Annular cascade for radial compressor development
US20160131146A1 (en) Pressure sensor system for calculating compressor mass flow rate using sensors at plenum and compressor entrance plane
CN101349283B (en) Axial flow fan model trial apparatus of turbine generator
Kong et al. Investigation on the leakage flow, windage heating and swirl development of rotating labyrinth seal in a compressor stator well
US11340184B2 (en) Engine component performance inspection sleeve and method of inspecting engine component
US10273965B2 (en) Method of extended thermodynamic turbine mapping via compressor inlet throttling
Romagnoli et al. Comparison Between the Steady Performance of Double-Entry and Twin-Entry Turbocharger Turbines
Brossman et al. Tailoring inlet flow to enable high accuracy compressor performance measurements
US11499430B2 (en) Turbine rotor blade, turbine, and tip clearance measurement method
Kim et al. Effect of fillet radius of receiver hole on the performance of gas turbine pre-swirl system
Johansson et al. Aerodynamic and heat transfer measurements on an intermediate turbine duct vane

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
RJ01 Rejection of invention patent application after publication

Application publication date: 20210402

RJ01 Rejection of invention patent application after publication