CN1701168A - Method for conditioning a compressor airflow and device therefor - Google Patents
Method for conditioning a compressor airflow and device therefor Download PDFInfo
- Publication number
- CN1701168A CN1701168A CN 02820762 CN02820762A CN1701168A CN 1701168 A CN1701168 A CN 1701168A CN 02820762 CN02820762 CN 02820762 CN 02820762 A CN02820762 A CN 02820762A CN 1701168 A CN1701168 A CN 1701168A
- Authority
- CN
- China
- Prior art keywords
- flow
- air
- stator
- compressor
- water
- 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
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
- F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
- F02C7/143—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages
- F02C7/1435—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages by water injection
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/212—Heat transfer, e.g. cooling by water injection
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention concerns a method for conditioning a compressor airflow (A, B) whereby an airflow (A, B) is sucked at an inlet (11) of an axial compressor (1) comprising, axially arranged a central rotor (2) and a stator (3) enclosing the rotor (2), and compressed on the path conveying said airflow towards the outlet (10). The sucked airflow (A, B) consists of a main flow (A) and a marginal flow (B) adjacent to the inner wall of the stator (3), and an exhaust orifice (6) located before the outlet (10) in the forward direction of flow enables the tapping of the marginal flow (B) to be used as cooling air. The temperature of the cooling air is simply and efficiently lowered by introducing water in the marginal flow (B) between the inlet (11) and the exhaust orifice (6), said water being evaporated when the marginal flow (B) is being cooled.
Description
Technical field
The present invention relates to the gas turbine technology field.It relates to according to the preprocess method of the compressor air of claim 1 preamble stream and implements the device of this method.
Background technique
As shown in unique accompanying drawing, Axial Flow Compressor 1 comprises a rotor 2 that can rotate around axle 9, a stator 3, and a plurality of blade ring parts (Schaufelkr nzen), the latter alternately is made up of the guide vane 5 that is fixed on the rotor blade 4 on the rotor 2 and be fixed on the stator 3.For the sake of simplicity, only express a blade for each blade ring in the figure.
Axial Flow Compressor 1 sucks air at an inlet, be compressed in the flow channel that air is constituted between the inwall of rotor 2 and stator 3 and with the pressure that increases from exporting 10 outflows.If this Axial Flow Compressor is the part of a gas-turbine plant, then the pressurized air that flows out in outlet 10 will be input in the next firing chamber, and be used for fuel combustion there.The hot gas that is produced will be depressurized when work done in next gas turbine.
Can be divided into two air-flows from the 11 inhaled air streams that enter the mouth, i.e. main air flow A, it flows through the intermediate portion of flow channel; And an edge air-flow B, it flows along the inwall of stator 3.If take out air in order to cool off purpose at the export mouth between inlet 11 and outlet 10 6 now, this air basic source is in edge air-flow B, and main air flow A is continued compression in export mouth 6 back.
The polytropic efficiency of Axial Flow Compressor 1 is not constant on the radially extension of rotor blade 4 and guide vane 5.Core air stream is than being compressed with better efficient at the air flow path that reaches on stator 3 inwalls on the rotor 2.Therefore the much higher temperature of air in the central gas stream on the air that export mouth 6 takes out (shunting) has than position 7.
For the situation that the air quantity of taking out from export mouth 6 should be used as the cooling air of a gas turbine, the temperature of this superelevation is disadvantageous.Simply this air stream (B) is cooled off again if replace,-this cools off the loss that causes gas-turbine plant efficient usually again, because the more fuel of needs-, what then conform with hope is: not only to avoid the described temperature superelevation between compression period, and even the temperature that will reach edge air-flow B descend.
Summary of the invention
Task of the present invention provides the preprocess method of a kind of compressor air stream, and the temperature of edge air-flow that it can be avoided the shortcoming in the known method and be implemented in the compression at export mouth place with simple and effective and efficient manner reduces, and the device that provides this method of enforcement.
This task will solve by whole features of claim 1 and 4.Core of the present invention is: between inlet and export mouth water is imported in the edge air-flow, this water evaporation is with cooling edge air-flow.To make the edge air-flow cooling of using as cooling air subsequently in simple mode thus, and can not influence other function of compressor thus.
Preferably realize like this: water is imported Axial Flow Compressor in this wise, so that constitute a thin moisture film on the inwall of stator.Especially, water sprays in the edge air-flow by the nozzle on a plurality of circumference that are arranged in stator with distributing.
Feature according to a preferred configuration of device of the present invention is: the device that is used to import water comprises a plurality of nozzles, and they are arranged on the circumference of stator with being distributed.
Other configuration will be by obtaining in the dependent claims.
Description of drawings
Describe the present invention below with reference to accompanying drawing in detail by embodiment.A unique accompanying drawing is represented the summary view according to a preferred embodiment of Axial Flow Compressor of the present invention.
Embodiment
The major component of the Axial Flow Compressor shown in the figure and function are made description in the explanation in conjunction with prior art.According to a preferred embodiment of the present invention, now will on this Axial Flow Compressor 1 by a plurality of flow channels of nozzle 8 between rotor 2 and stator 3 that are arranged on stator 3 circumference in transporting water (H
2O).Water by 8 inputs of these nozzles is because the air stream in the flow channel forms a thin moisture film on the inwall of stator 3.This moisture film forms to contact to reach with edge air-flow B and evaporates under the situation that edge air-flow B is cooled.Provide the edge air-flow B that is cooled to be used as the cooling air of back level gas turbine at export mouth 6 then.
These nozzles 8 are preferably disposed between adjacent rotor blade 4 and the guide vane 5, can constitute moisture film well thus.When nozzle 8 was set at the face after a while (downstream) of inlet 11 of Axial Flow Compressor 1 on the airflow direction, the cooling action of the moisture film of evaporation was maximum in addition.
Claims (7)
1. compressor air flows (A, B) preprocess method, in the method, in a coaxial configuration, comprise center rotor (2) and surround in the Axial Flow Compressor (1) of stator (3) of this rotor (2), locate to suck air stream (A at an inlet (11), B) and at this air stream on the path of outlet (10) be compressed, wherein inhaled air flows (A, B) form by a main air flow (A) and an edge air-flow (B) that is positioned on stator (3) inwall, and from being positioned at outlet (10) export mouth (6) before at flow direction by described edge air-flow (B) taking-up air, to be used as cooling air, it is characterized in that: between inlet (11) and export mouth (6) water is imported in the edge air-flow (B), this water evaporates under the situation that edge air-flow (B) is cooled.
2. according to the method for claim 1, it is characterized in that: water is imported in the Axial Flow Compressor (1), so that constitute a thin moisture film on the inwall of stator (3).
3. according to the method for claim 2, it is characterized in that: water sprays in the edge air-flow (B) by the nozzle (8) on a plurality of circumference that are arranged in stator (3) with distributing.
4. be used to implement device, it is characterized in that: on the stator (3) of Axial Flow Compressor (1), be provided with the device (8) that is used for water is imported edge air-flow (B) according to the method for claim 1.
5. according to the device of claim 4, it is characterized in that: the device that is used to import water comprises a plurality of nozzles (8), and they are arranged on the circumference of stator (3) with being distributed.
6. according to the device of claim 5, it is characterized in that: Axial Flow Compressor (1) has impeller assembly, and it comprises rotor blade (4) and the guide vane (5) that is arranged alternately; And these nozzles (8) are set between adjacent rotor blade (4) and the guide vane (5).
7. according to the device of claim 5 or 6, it is characterized in that: these nozzles (8) are set at the face after a while of the inlet (11) of Axial Flow Compressor on the airflow direction (1).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CH19092001 | 2001-10-17 | ||
| CH1909/01 | 2001-10-17 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1701168A true CN1701168A (en) | 2005-11-23 |
Family
ID=4566747
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 02820762 Pending CN1701168A (en) | 2001-10-17 | 2002-10-02 | Method for conditioning a compressor airflow and device therefor |
Country Status (3)
| Country | Link |
|---|---|
| EP (1) | EP1436491A1 (en) |
| CN (1) | CN1701168A (en) |
| WO (1) | WO2003033890A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103452668A (en) * | 2012-06-01 | 2013-12-18 | 株式会社日立制作所 | Axial compressor and gas turbine having axial compressor |
| CN113266533A (en) * | 2021-06-02 | 2021-08-17 | 安徽三联学院 | Aerogenerator gear box with heat radiation structure |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| IT454098A (en) * | 1948-02-27 | |||
| DE4442936A1 (en) * | 1994-12-02 | 1996-06-05 | Abb Patent Gmbh | Operating stationary gas turbine installation for silo combustion chamber |
| EP0903483A1 (en) * | 1997-09-17 | 1999-03-24 | Romabau AG | Method and device for cooling a gas flow in a gas turbine |
| US6553753B1 (en) * | 1998-07-24 | 2003-04-29 | General Electric Company | Control systems and methods for water injection in a turbine engine |
| DE19900026B4 (en) * | 1999-01-02 | 2016-01-21 | Alstom Technology Ltd. | Gas turbine with steam injection |
| DE10027842A1 (en) * | 2000-06-05 | 2001-12-20 | Alstom Power Nv | Gas turbine layout cooling system bleeds portion of film cooling air through turbine blade via inlet or outlet edge borings for direct blade wall service. |
-
2002
- 2002-10-02 WO PCT/IB2002/004068 patent/WO2003033890A1/en not_active Application Discontinuation
- 2002-10-02 CN CN 02820762 patent/CN1701168A/en active Pending
- 2002-10-02 EP EP02765281A patent/EP1436491A1/en not_active Withdrawn
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103452668A (en) * | 2012-06-01 | 2013-12-18 | 株式会社日立制作所 | Axial compressor and gas turbine having axial compressor |
| CN103452668B (en) * | 2012-06-01 | 2015-12-09 | 三菱日立电力系统株式会社 | Axial flow compressor and possess the gas turbine of this axial flow compressor |
| US9644642B2 (en) | 2012-06-01 | 2017-05-09 | Mitsubishi Hitachi Power Systems, Ltd. | Axial compressor and gas turbine having axial compressor |
| CN113266533A (en) * | 2021-06-02 | 2021-08-17 | 安徽三联学院 | Aerogenerator gear box with heat radiation structure |
Also Published As
| Publication number | Publication date |
|---|---|
| EP1436491A1 (en) | 2004-07-14 |
| WO2003033890A1 (en) | 2003-04-24 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US6973771B2 (en) | Diffuser for terrestrial or aviation gas turbine | |
| US6012279A (en) | Gas turbine engine with water injection | |
| US4711084A (en) | Ejector assisted compressor bleed | |
| SU1111690A3 (en) | Method for producing energy in internal combustion engine and internal combustion engine | |
| US6484508B2 (en) | Methods for operating gas turbine engines | |
| EP1167722A3 (en) | Methods and apparatus for delivering cooling air within gas turbines | |
| US20060181029A1 (en) | Cooling arrangement for brush seal | |
| JPH04209934A (en) | Air cooling turbine engine and cooling method therefor | |
| US20030079478A1 (en) | High pressure turbine blade cooling scoop | |
| CN102686832A (en) | Method for cooling turbine stators and cooling system for implementing said method | |
| US7553122B2 (en) | Self-aspirated flow control system for centrifugal compressors | |
| US20050193732A1 (en) | Method and apparatus for cooling turbomachinery components | |
| CA2464209A1 (en) | Turbine engine with air cooled turbine | |
| JP4012507B2 (en) | Double flow compressor | |
| US10323571B2 (en) | Method and system for inlet guide vane heating | |
| CN107084004A (en) | Impact opening for turbine engine components | |
| US20100098553A1 (en) | Aspirated impeller | |
| US20080240904A1 (en) | Method of Pumping Gaseous Matter via a Supersonic Centrifugal Pump | |
| US8256202B1 (en) | High bypass turbofan | |
| EP1520960A2 (en) | Cooling air supply | |
| GB742477A (en) | Improvements in or relating to bladed stator or rotor constructions for fluid machines such as axial-flow turbines or compressors | |
| US20040081556A1 (en) | Blade passive cooling feature | |
| KR101279269B1 (en) | A turbine part of a turbocompressor and a method of avoiding carbon build-up in the turbine part of a turbocompressor | |
| CN101008402A (en) | Method and apparatus for reducing axial compressor blade tip flow | |
| CN1701168A (en) | Method for conditioning a compressor airflow and device therefor |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |