CN106194828A - A kind of bleed structure for compressor rotor inner chamber - Google Patents
A kind of bleed structure for compressor rotor inner chamber Download PDFInfo
- Publication number
- CN106194828A CN106194828A CN201610546118.3A CN201610546118A CN106194828A CN 106194828 A CN106194828 A CN 106194828A CN 201610546118 A CN201610546118 A CN 201610546118A CN 106194828 A CN106194828 A CN 106194828A
- Authority
- CN
- China
- Prior art keywords
- rotor
- bleed
- inner chamber
- compressor
- groove
- 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
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
- F04D29/286—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors multi-stage rotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/58—Cooling; Heating; Diminishing heat transfer
- F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
Abstract
The present invention relates to a kind of bleed structure for compressor rotor inner chamber, rotor at compressor is installed and is offered multiple bleed groove on limit, bleed air-flow is communicated in rotor internal cavity and rotor exocoel by described bleed groove, compressor rotor, rotor installation limit and next stage compressor rotor is fixedly connected by connector.Bleed air-flow is introduced rotor internal cavity by the bleed structure for compressor rotor inner chamber of the present invention, heat for compressor later stages rotor internal cavity, reduce the thermograde of rotor disk, thus reduce the rotor additional stress brought by thermograde, in limited structure space, do not affect the safe and reliable connection of rotor, while not increasing additional knot component, it is achieved that the bleed of rotor internal cavity, reduce the rotor additional stress that rotor disk brings due to thermograde, structural safety, reliability is high.
Description
Technical field
The invention belongs to fanjet technical field, particularly relate to a kind of bleed for compressor rotor inner chamber and tie
Structure.
Background technology
Along with the development of turbofan designing technique, the raising of turbofan thrust-weight ratio, compressor portion
The pressure ratio of part steps up, and the temperature of compressor part later stages improves the most accordingly.This results in compressor later stages rotor and exists
While bearing higher centrifugal load, also it is subjected to the additional stress brought due to the thermograde of rotor.And due to electromotor
Weight has the lightest requirement, and the stress of rotor disk, under light weight indicator requires, is difficult to meet strength stress storage
Standby requirement.Need to introduce hot-air at rotor internal cavity, to reduce the thermograde of wheel disc, reduce the rotor brought by thermograde
The additional stress of wheel disc.But this also brings certain difficulty to structure design, in the case of limited structure space, meet simultaneously
The reliability of rotor connection structure, be also satisfied rotor internal cavity bleed requirements simultaneously.
Summary of the invention
It is an object of the invention to provide a kind of bleed structure for compressor rotor inner chamber, be used for solving the problems referred to above.
For reaching above-mentioned purpose, the technical solution used in the present invention is: a kind of bleed for compressor rotor inner chamber is tied
Structure, offers multiple bleed groove on the rotor installation limit of compressor, and bleed air-flow is communicated in rotor by described bleed groove
Chamber and rotor exocoel, be fixedly connected compressor rotor, rotor installation limit and next stage compressor rotor by connector.
Further, described bleed groove is rectangular channel or semi-circular groove.
Further, the end face radial direction that described bleed groove installs limit at described rotor is uniformly distributed.
Further, described bleed groove is in staggered distribution with connector, to ensure bonding strength.
Further, the end face at bleed groove place contacts with next stage compressor rotor.
Further, the area that described bleed groove is installed on the end face of limit at described rotor installs limit end face less than or equal to rotor
Long-pending 50%.
Further, the fluting equivalent of described bleed groove is more than or equal to specified amount of air entrainment, and described fluting equivalent refers to draw
Entraining air stream enters total amount of air entrainment of bleed inner chamber by all bleed concentrated flows.
The bleed structure for compressor rotor inner chamber of the present invention uses opens tap air channel in rotor connection installation site
Method, will meet the uniform temperature of design requirement bleed air-flow introduce rotor internal cavity, for compressor later stages rotor internal cavity
Heating, reduces the thermograde of rotor disk, thus reduces the rotor additional stress brought by thermograde, and the present invention is used for
The bleed structure of compressor rotor inner chamber, in limited structure space, does not affect the safe and reliable connection of rotor, does not increase extra
While structural member, it is achieved that the bleed of rotor internal cavity, reducing that rotor that rotor disk brings due to thermograde is additional should
Power, structural safety, reliability is high.
Accompanying drawing explanation
Accompanying drawing herein is merged in description and constitutes the part of this specification, it is shown that meet the enforcement of the present invention
Example, and for explaining the principle of the present invention together with description.
Fig. 1 is the rotor internal cavity bleed structural representation according to one embodiment of the invention.
Fig. 2 is the bleed channel structure schematic diagram installed on limit according to one embodiment of the invention.
Fig. 3 is that avris view installed by the rotor according to one embodiment of the invention.
Fig. 4 is that limit front view installed by the rotor according to one embodiment of the invention.
Wherein, 1-compressor rotor, 2-rotor installation limit, 3-bleed air-flow, 4-rotor exocoel, 5-rotor internal cavity, 21-draws
Air drain.
Detailed description of the invention
Clearer for the purpose making the present invention implement, technical scheme and advantage, below in conjunction with in the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, the most identical or class
As label represent same or similar element or there is the element of same or like function.Described embodiment is the present invention
A part of embodiment rather than whole embodiments.The embodiment described below with reference to accompanying drawing is exemplary type, it is intended to use
In explaining the present invention, and it is not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under not making creation type work premise, broadly falls into the scope of protection of the invention.Under
Face combines accompanying drawing and is described in detail embodiments of the invention.
In describing the invention, it is to be understood that term " " center ", " longitudinally ", " laterally ", "front", "rear",
The orientation of the instruction such as "left", "right", " vertically ", " level ", " top ", " end ", " interior ", " outward " or position relationship are for based on accompanying drawing institute
The orientation shown or position relationship, be for only for ease of and describe the present invention and simplify description rather than instruction or the dress of hint indication
Put or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that protect the present invention
The restriction of scope.
Being the bleed structure for compressor rotor inner chamber of the present invention as shown in Figures 1 and 2, the rotor at compressor is pacified
Offering multiple bleed groove 21 on rim 2, bleed air-flow 3 flows to rotor internal cavity 5 by bleed groove 21 from rotor exocoel 5, passes through
The compressor rotor of compressor rotor 1, rotor installation limit 2 and next stage is fixedly connected by connecting bolt.The pressure of the present invention
Mechanism of qi rotor internal cavity bleed structure, uses and connects, at rotor, the method that bleed groove 21 is offered in the position installed, can meet design
The compressed gas by uniform temperature (i.e. bleed air-flow 3) of demand introduces rotor internal cavity 5, adds for compressor later stages rotor internal cavity
Heat, reduces the thermograde of rotor disk, thus reduces the rotor additional stress brought by thermograde, and at limited rotor
In connection space, while meeting the safe and reliable connection of rotor, it is provided that the tap air channel of rotor internal cavity 5.
In the present invention, bleed groove 21 is rectangular channel or semi-circular groove, and the groove of this structure is easy to machining.
Additionally, the end face radial direction that bleed groove 21 installs limit 2 at rotor is uniformly distributed, bleed air-flow 3 can be made to flow into and to turn
After sub-inner chamber 4, heat is carried out uniform radiating treatment.Bleed groove 21 is in staggered distribution with connector, to ensure bonding strength, this
In embodiment, connector uses bolt.Further, bleed groove 21 installs the area on the end face of limit 2 less than or equal to turning at rotor
Son installs 50% that there is the area of the one end causing groove 21 on limit 2, the most as shown in Figure 3 and Figure 4, causes the area of groove 21 to account for rotor peace
The area of rim 2 is less than half (as shown in Figure 4).Bleed groove 21 to stagger with bolt link position cloth in a circumferential direction
Put, and stagger a certain distance with bolt connecting hole limit, and cause the requirement of the groove 21 area on end face be for
Ensure that the stress on bolt connecting hole limit meets margin of safety requirement.
It addition, in the bleed structure for compressor rotor inner chamber of the present invention, the fluting equivalent of bleed groove 21 is more than
Equal to specified amount of air entrainment, fluting equivalent is referred to bleed air-flow 3 and is entered the amount of air entrainment of bleed inner chamber 5 by all bleed concentrated flows.I.e.
The bleed structure for compressor rotor inner chamber of the present invention uses and installs, at rotor, the method offering bleed groove 21 on limit 2, will
Meet and use the compressed gas of temperature requirement to introduce rotor internal cavity, the bleed equivalent aera air system to be met that bleed groove 21 is total
The requirement of amount of air entrainment, bleed groove 21 to be controlled accounts for the percentage ratio in cooperation face, whole installation limit, safe and reliable to meet rotor
The nip requirement connected, can improve the nip at this cooperation face place in the case of necessity.
The bleed structure for compressor rotor inner chamber of the present invention can ensure the safe and reliable connection of whole rotor, and
On the premise of the most additionally increasing structural member, increase the tap air channel of rotor internal cavity 5.
The bleed structure for compressor rotor inner chamber of the present invention is compared with conventional bleed structure, in limited structure
In space, do not affect the safe and reliable connection of rotor, while not increasing additional knot component, it is achieved that the bleed of rotor internal cavity 5, fall
The additional stress of the compressor rotor 1 that low rotor disk brings due to thermograde, has structural safety, reliability high etc. excellent
Point, and the bleed structure for compressor rotor inner chamber of the present invention is possible not only to directly apply to calming the anger of aero-engine
On machine parts, it is possible to be applied to other relevant speciality.
The above, the only optimum detailed description of the invention of the present invention, but protection scope of the present invention is not limited thereto,
Any those familiar with the art in the technical scope that the invention discloses, the change that can readily occur in or replacement,
All should contain within protection scope of the present invention.Therefore, protection scope of the present invention should be with the protection model of described claim
Enclose and be as the criterion.
Claims (7)
1. the bleed structure for compressor rotor inner chamber, it is characterised in that the rotor at compressor is installed and opened on limit (2)
Being provided with multiple bleed groove (21), bleed air-flow (3) is communicated in rotor internal cavity (4) and rotor exocoel by described bleed groove (21)
(5), by connector, compressor rotor (1), rotor installation limit (2) and next stage compressor rotor are fixedly connected.
Bleed structure for compressor rotor inner chamber the most according to claim 1, it is characterised in that described bleed groove
(21) it is rectangular channel or semi-circular groove.
Bleed structure for compressor rotor inner chamber the most according to claim 1, it is characterised in that described bleed groove
(21) the end face radial direction at described rotor installation limit (2) is uniformly distributed.
Bleed structure for compressor rotor inner chamber the most according to claim 3, it is characterised in that described bleed groove
(21) it is in staggered distribution with connector, to ensure bonding strength.
Bleed structure for compressor rotor inner chamber the most according to claim 1, it is characterised in that bleed groove (21) institute
End face contact with next stage compressor rotor.
Bleed structure for compressor rotor inner chamber the most according to claim 1, it is characterised in that described bleed groove
(21) at described rotor, the area on limit (2) end face is installed and the 50% of limit (2) end area is installed less than or equal to rotor.
Bleed structure for compressor rotor inner chamber the most according to claim 1, it is characterised in that described bleed groove
(21) fluting equivalent is more than or equal to specified amount of air entrainment, and described fluting equivalent refers to bleed air-flow (3) by all bleed grooves
Flow into total amount of air entrainment of bleed inner chamber (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610546118.3A CN106194828A (en) | 2016-07-12 | 2016-07-12 | A kind of bleed structure for compressor rotor inner chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610546118.3A CN106194828A (en) | 2016-07-12 | 2016-07-12 | A kind of bleed structure for compressor rotor inner chamber |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106194828A true CN106194828A (en) | 2016-12-07 |
Family
ID=57476646
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610546118.3A Pending CN106194828A (en) | 2016-07-12 | 2016-07-12 | A kind of bleed structure for compressor rotor inner chamber |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106194828A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111577652A (en) * | 2020-05-11 | 2020-08-25 | 中国航发沈阳发动机研究所 | Drum barrel structure and compressor rotor disc connecting structure thereof |
| EP3851632A1 (en) * | 2020-01-20 | 2021-07-21 | Raytheon Technologies Corporation | Gas turbine engine rotor stack with bushing having adaptive airflow temperature metering |
| CN113847280A (en) * | 2021-10-10 | 2021-12-28 | 中国航发沈阳发动机研究所 | Compressor rotor interstage bleed air structure |
| CN113898610A (en) * | 2021-10-10 | 2022-01-07 | 中国航发沈阳发动机研究所 | Gas-entraining structure for disk center of rotor disk of compressor |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3647313A (en) * | 1970-06-01 | 1972-03-07 | Gen Electric | Gas turbine engines with compressor rotor cooling |
| US6361277B1 (en) * | 2000-01-24 | 2002-03-26 | General Electric Company | Methods and apparatus for directing airflow to a compressor bore |
| CN102016233A (en) * | 2008-04-24 | 2011-04-13 | 斯奈克玛 | Centripetal air bleed from a turbomachine compressor rotor |
-
2016
- 2016-07-12 CN CN201610546118.3A patent/CN106194828A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3647313A (en) * | 1970-06-01 | 1972-03-07 | Gen Electric | Gas turbine engines with compressor rotor cooling |
| US6361277B1 (en) * | 2000-01-24 | 2002-03-26 | General Electric Company | Methods and apparatus for directing airflow to a compressor bore |
| CN102016233A (en) * | 2008-04-24 | 2011-04-13 | 斯奈克玛 | Centripetal air bleed from a turbomachine compressor rotor |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3851632A1 (en) * | 2020-01-20 | 2021-07-21 | Raytheon Technologies Corporation | Gas turbine engine rotor stack with bushing having adaptive airflow temperature metering |
| US11352903B2 (en) | 2020-01-20 | 2022-06-07 | Raytheon Technologies Corporation | Rotor stack bushing with adaptive temperature metering for a gas turbine engine |
| US11555416B2 (en) | 2020-01-20 | 2023-01-17 | Raytheon Technologies Corporation | Rotor stack bushing with adaptive temperature metering for a gas turbine engine |
| CN111577652A (en) * | 2020-05-11 | 2020-08-25 | 中国航发沈阳发动机研究所 | Drum barrel structure and compressor rotor disc connecting structure thereof |
| CN111577652B (en) * | 2020-05-11 | 2021-09-03 | 中国航发沈阳发动机研究所 | Drum barrel structure and compressor rotor disc connecting structure thereof |
| CN113847280A (en) * | 2021-10-10 | 2021-12-28 | 中国航发沈阳发动机研究所 | Compressor rotor interstage bleed air structure |
| CN113898610A (en) * | 2021-10-10 | 2022-01-07 | 中国航发沈阳发动机研究所 | Gas-entraining structure for disk center of rotor disk of compressor |
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| C06 | 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: 20161207 |
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| RJ01 | Rejection of invention patent application after publication |