Clamped HPC seal ring

Patent metadata

Field	Value
Publication number	US-10006466-B2
Application number	US-201514685225-A
Country	US
Kind code	B2
Filing date	Apr 13, 2015
Priority date	Apr 13, 2015
Publication date	Jun 26, 2018
Grant date	Jun 26, 2018

Abstract

A seal ring for use between an integrally bladed rotor and a hub rotor of a compressor section of a gas turbine engine includes an arm configured to be positioned between the integrally bladed rotor and the hub rotor, such that the seal ring is removably coupled to the integrally bladed rotor and the hub rotor in response to a compressive force applied to the arm by the integrally bladed rotor and the hub rotor. The seal ring also includes a first blade coupled to the arm and configured to form a seal between a first volume and a second volume.

First claim

The invention claimed is:

1. A seal ring for use between an integrally bladed rotor and a hub rotor of a compressor section of a gas turbine engine, the seal ring comprising:
a radial arm configured to be positioned axially between the integrally bladed rotor and the hub rotor;
an axial arm configured to be positioned radially between the integrally bladed rotor and the hub rotor, wherein the seal ring is removably coupled to the integrally bladed rotor and the hub rotor in response to a compressive force applied to the radial arm and the axial arm by the integrally bladed rotor and the hub rotor; and
a first blade coupled to the axial arm and configured to form a seal between a first volume and a second volume;
wherein the seal ring is configured to rotate at a same angular velocity with both the integrally bladed rotor and the hub rotor.

2. The seal ring of claim 1 , wherein the seal ring is positioned about an axis and configured to rotate about the axis in response to the integrally bladed rotor and the hub rotor rotating about the axis.

3. The seal ring of claim 1 , wherein the compressor section is a high pressure compressor section.

4. The seal ring of claim 1 , wherein the hub rotor is configured to be coupled to an outer shaft and the seal ring is configured to be decoupled from the integrally bladed rotor and the hub rotor by decoupling the hub rotor from the outer shaft.

5. A system comprising:
an integrally bladed rotor of a compressor section of a gas turbine engine, the integrally bladed rotor configured to rotate about an axis;
a hub rotor positioned aft of the integrally bladed rotor and configured to rotate about the axis; and
a seal ring configured to be positioned between the integrally bladed rotor and the hub rotor and removably coupled to the integrally bladed rotor and the hub rotor via a compressive force and configured to rotate about the axis at a same angular velocity as both the integrally bladed rotor and the hub rotor, wherein the seal ring comprises a radial arm positioned axially between the integrally bladed rotor and the hub rotor and an axial arm positioned radially between the integrally bladed rotor and the hub rotor.

6. The system of claim 5 , wherein the seal ring defines a first blade.

7. The system of claim 5 , wherein the integrally bladed rotor includes a rotor disk portion and a blade portion.

8. The system of claim 5 , wherein the compressor section is a high pressure compressor section.

9. The system of claim 5 , further comprising an outer shaft and wherein the hub rotor is configured to be coupled to the outer shaft and the seal ring is configured to be decoupled from the integrally bladed rotor and the hub rotor by decoupling the hub rotor from the outer shaft.

10. A seal ring for use between an integrally bladed rotor and a hub rotor of a compressor section of a gas turbine engine, the seal ring comprising:
a radial arm configured to be axially positioned between the integrally bladed rotor and the hub rotor; and
an axial arm configured to be radially positioned between the integrally bladed rotor and the hub rotor, such that the seal ring is removably coupled to the integrally bladed rotor and the hub rotor in response to a compressive force applied to the seal ring by the integrally bladed rotor and the hub rotor;
wherein the seal ring comprises at least one of:
the radial arm having a forward axial face configured to align with and contact a rotor axial face of the integrally bladed rotor and an aft axial face configured to align with and contact a hub axial face of the hub rotor; and
the axial arm having an outer radial face configured to align with and contact a rotor radial face of the integrally bladed rotor and an inner radial face configured to align with and contact a hub radial face of the hub rotor.

11. The seal ring of claim 10 , wherein the axial arm defines a first blade and a second blade.

12. The seal ring of claim 10 , wherein the seal ring is positioned about an axis and configured to rotate about the axis in response to the integrally bladed rotor and the hub rotor rotating about the axis.

13. The seal ring of claim 10 , wherein the compressor section is a high pressure compressor section.

Assignees

• United Technologies Corp

Inventors

• Wilber John E
• Reilly Bernard J

Classifications

• F01D5/06 Primary

  Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections {(F01D5/022, F01D5/023 take precedence)} · CPC title

• F04D29/083 Primary

  especially adapted for elastic fluid pumps · CPC title

• F05D2240/55

  Seals · CPC title

• F01D11/001

  for sealing space between stator blade and rotor · CPC title

• F01D5/34

  Rotor-blade aggregates of unitary construction {, e.g. formed of sheet laminae; (discs formed of sheet laminae F01D5/028; ceramic materials F01D5/284, composite materials F01D5/282)} · CPC title