RU2008102810A - GAS-TURBINE ENGINE TURBINE ROTOR - Google Patents
GAS-TURBINE ENGINE TURBINE ROTOR Download PDFInfo
- Publication number
- RU2008102810A RU2008102810A RU2008102810/06A RU2008102810A RU2008102810A RU 2008102810 A RU2008102810 A RU 2008102810A RU 2008102810/06 A RU2008102810/06 A RU 2008102810/06A RU 2008102810 A RU2008102810 A RU 2008102810A RU 2008102810 A RU2008102810 A RU 2008102810A
- Authority
- RU
- Russia
- Prior art keywords
- disk
- flange
- disks
- stage
- turbine rotor
- Prior art date
Links
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 title 1
- 241000826860 Trapezium Species 0.000 claims abstract 2
- 150000001875 compounds Chemical class 0.000 claims abstract 2
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Ротор турбины газотурбинного двигателя с дисками первой и второй ступеней и установленными в междисковой полости передним и задним промежуточным дисками, отличающийся тем, что диск первой ступени выполнен с Г-образным фланцем, фланец диска второй ступени по внешней поверхности выполнен с упругим элементом, кольцевым ребром осевой фиксации ступицы заднего промежуточного диска и конусной внутренней поверхностью, а соединение фланцев дисков первой и второй ступеней осуществляют с помощью осевых шпилек и гаек, при этом фланец диска второй ступени включает множество расположенных напротив каждого соединения фланцев радиальных окон, поперечное сечение которых имеет форму равнобокой трапеции со скругленными углами и широким основанием со стороны гаек, причем один из дисков закреплен на валу ротора турбины шлицевым соединением.A turbine rotor of a gas turbine engine with first and second stage disks and front and rear intermediate disks installed in the inter-disk cavity, characterized in that the first stage disk is made with a L-shaped flange, the second stage disk flange is made on the outer surface with an elastic element, an axial annular rib fixing the hub of the rear intermediate disk and the conical inner surface, and the connection of the flanges of the disks of the first and second stages is carried out using axial studs and nuts, while the disk flange is second It includes a plurality of stages arranged opposite each compound radial flange windows, the cross section of which has the shape of an equilateral trapezium with rounded corners and a wide base by screws, wherein one of the discs is fixed on the turbine rotor shaft spline.
Claims (1)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2008102810/06A RU2369746C1 (en) | 2008-01-24 | 2008-01-24 | Gas turbine engine rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2008102810/06A RU2369746C1 (en) | 2008-01-24 | 2008-01-24 | Gas turbine engine rotor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| RU2008102810A true RU2008102810A (en) | 2009-07-27 |
| RU2369746C1 RU2369746C1 (en) | 2009-10-10 |
Family
ID=41048142
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| RU2008102810/06A RU2369746C1 (en) | 2008-01-24 | 2008-01-24 | Gas turbine engine rotor |
Country Status (1)
| Country | Link |
|---|---|
| RU (1) | RU2369746C1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110878762A (en) * | 2019-12-13 | 2020-03-13 | 中国船舶重工集团公司第七0三研究所 | Pin-connected gas turbine compressor rotor and installation method thereof |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2453709C1 (en) * | 2010-12-23 | 2012-06-20 | Открытое акционерное общество "Авиадвигатель" | Gas turbine engine turbine rotor |
| RU2684355C1 (en) * | 2018-07-05 | 2019-04-08 | Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Gas turbine engine low-pressure turbine (lpt) (versions), rotor shaft connection unit with lpt disc, lpt rotor air cooling path and air feeding apparatus for cooling lpt rotor blades |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4582467A (en) * | 1983-12-22 | 1986-04-15 | United Technologies Corporation | Two stage rotor assembly with improved coolant flow |
| RU2001288C1 (en) * | 1990-06-18 | 1993-10-15 | Акционерное общество открытого типа "Авиадвигатель" | Two-stage turbine rotor |
| US6283712B1 (en) * | 1999-09-07 | 2001-09-04 | General Electric Company | Cooling air supply through bolted flange assembly |
| RU2224892C2 (en) * | 2002-05-06 | 2004-02-27 | Открытое акционерное общество "Авиадвигатель" | Gas-turbine engine with two-stage gas turbine |
| RU2232901C2 (en) * | 2002-08-20 | 2004-07-20 | Открытое акционерное общество "Авиадвигатель" | Turbine of gas-turbine engine |
| RU2263809C2 (en) * | 2003-08-04 | 2005-11-10 | Открытое акционерное общество "Авиадвигатель" | Multistage gas turbine |
-
2008
- 2008-01-24 RU RU2008102810/06A patent/RU2369746C1/en not_active IP Right Cessation
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110878762A (en) * | 2019-12-13 | 2020-03-13 | 中国船舶重工集团公司第七0三研究所 | Pin-connected gas turbine compressor rotor and installation method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| RU2369746C1 (en) | 2009-10-10 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MM4A | The patent is invalid due to non-payment of fees |
Effective date: 20110125 |