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Segmented fluid seal assembly

Inactive Publication Date: 2008-02-21
UNITED TECH CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

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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  • Segmented fluid seal assembly
  • Segmented fluid seal assembly
  • Segmented fluid seal assembly

Examples

Experimental program
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Embodiment Construction

[0020]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.

[0021]FIG. 2 illustrates a portion of a cross-section of a typical turbine engine rotor showing a rotor disk 26, which is one of several defining a turbine rotor. Each rotor disk 26 of the rotor 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 stationary stator vanes 30 extend radially inwardly between the rotor blades 28 of axially adjacent rotor disks 26, as known.

[0022]Each rotor disk 26 includes a disk rim 32. The disk rim ...

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PUM

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Abstract

A rotor assembly for a turbine engine includes a rotor disk having rotor blades mounted about the circumference and rotatable about a central longitudinal axis. A fluid seal extends about the circumference of the rotor disk in close proximity to a stationary component to separate the space between the rotor blades and a stationary component into separate cavities. The fluid seal includes a plurality of disk seal segments and a plurality of blade seal segments. The disk seal segments each attach to the rotor disk between the rotor blades. The blade seal segments attach to the blades. After the blades are assembled the blade seal segments and the disk seal segments align to form a segmented, ring-like fluid seal 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 Ser. 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. The disclosures of each aforementioned application are incorporated herein by reference.BACKGROUND OF THE INVENTION[0002]The invention generally relates to an arrangement for loading and retaining a segmented fluid seal assembly within a gas turbine engine.[0003]Turbine engines include high and low rotor spools comprising multiple rotor disks. Fluid seals are formed integrally into each rotor disk to contact stator components, such as a stator vane, support or tangential on-board injector. The seals restrict leakage of ...

Claims

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Application Information

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IPC IPC(8): F01D11/00
CPCF01D11/001F05D2260/30F05D2230/60F01D11/02F01D5/3007F01D5/323
Inventor ALVANOS, IOANNIS
Owner UNITED TECH CORP
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