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Fluid brush seal with segment seal land

a technology of segment sealing and fluid brush, applied in the direction of liquid fuel engines, machines/engines, stators, etc., can solve problems such as unduly complex, and achieve the effect of reducing the wear on the rotor disk

Inactive Publication Date: 2008-04-24
UNITED TECH CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

[0006]An example turbine engine rotor according to this invention includes an arrangement for incorporating a fluid seal assembly while reducing wear on the rotor disk.
[0009]Each disk land segment has a first interlocking feature interfitting with a second interlocking feature on the blade land segments to align the land segments and reduce circumferential and radial fluid leaks.

Problems solved by technology

This is unduly complex.
Also, during operation of the engine, the fluid seal may contact an abradable material on the stationary components, causing wear.

Method used

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  • Fluid brush seal with segment seal land
  • Fluid brush seal with segment seal land
  • Fluid brush seal with segment seal land

Examples

Experimental program
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Effect test

Embodiment Construction

[0018]FIG. 1 is a schematic view of a turbine engine 10. Air is pulled into the turbine engine 10 by a fan 12 and flows through a low pressure compressor 14 and a high pressure compressor 16. Fuel is mixed with the air, and combustion occurs within the combustor 18. Exhaust from combustion flows through a high pressure turbine 20 and a low pressure turbine 22 prior to leaving the engine through an exhaust nozzle 24.

[0019]FIG. 2 illustrates a portion of a cross-section of a typical turbine engine turbine, showing a rotor disk 26, which is one of several defining a rotor. Each rotor disk 26 rotates about an axis A located along the longitudinal centerline of the turbine engine 10. A plurality of rotor blades 28 are mounted about the circumference of each rotor disk 26. A plurality of stator vanes 30 extend between the rotor blades 28 of axially adjacent rotor disks 26, as shown.

[0020]Each rotor disk 26 includes a disk rim 32. The disk rim 32 secures the rotor blades 28. A fluid seal 3...

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PUM

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Abstract

A turbine rotor for a turbine engine includes multiple rotor disks having rotor blades mounted about the circumference of each of the rotor disks. A fluid seal extends about the circumference of each rotor disk in close proximity to a stationary component of the rotor to separate the space between the rotor blades and a stationary component into separate cavities. The fluid seal includes a seal land on the rotor disk and a brush seal extending from the stationary component. A plurality of disk land segments and a plurality of blade land segments form the seal land. The disk seal segments are located on the rotor disk between the rotor blades. The blade land segments are located on the rotor blades. After the rotor blades are assembled, the blade land segments and the disk land segments fit together to form a segmented ring-like seal land around the circumference of the rotor disk.

Description

[0001]This application discloses subject matter related to co-pending US patent applications “HAMMERHEAD FLUID SEAL” (U.S. patent application Ser. No. 11 / 146,801), “COMBINED BLADE ATTACHMENT AND DISK LUG FLUID SEAL” (U.S. patent application Ser. No. 11 / 146,798) and “BLADE NECK FLUID SEAL” (U.S. patent application No. 11 / 146,660), each filed on Jul. 7, 2005, and “INTEGRATED BLADED FLUID SEAL” (U.S. patent application Ser. No. 11 / 260,357) filed on Oct. 27, 2005.BACKGROUND OF THE INVENTION[0002]The invention generally relates to an arrangement for fluid seals within a gas turbine engine.[0003]Turbine engines include high and low pressure rotor spools comprising multiple rotor disks. Fluid seals are formed integrally into each rotor disk to contact stator components, such as a tangential on-board injector. The seals restrict leakage of compressed air from between the stator component and the rotor disks and separate the lower pressure gaspath air from high pressure air used for cooling....

Claims

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Application Information

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IPC IPC(8): F01D11/00
CPCF01D5/3007F05D2240/56F01D11/001
Inventor ALVANOS, IOANNISVIRTUE, JOHN P.
Owner UNITED TECH CORP