Reduced stress rotor interface

Patent metadata

Field	Value
Publication number	US-10125785-B2
Application number	US-201514885373-A
Country	US
Kind code	B2
Filing date	Oct 16, 2015
Priority date	Oct 16, 2015
Publication date	Nov 13, 2018
Grant date	Nov 13, 2018

Abstract

A bladed rotor and a hub rotor for a gas turbine are provided. A bladed rotor may comprise a rotor interface comprising a radially inward surface, wherein the rotor interface comprises a constant diameter zone; and a reduced stress zone located adjacent to and aft of the constant diameter zone. A hub rotor may comprise a hub interface comprising a radially outward surface, wherein the hub interface comprises, a constant diameter zone, and a reduced stress zone located adjacent to and aft of the constant diameter zone.

First claim

What is claimed is:

1. A bladed rotor for a gas turbine engine, the gas turbine engine comprising a center axis extending from forward to aft, wherein the bladed rotor comprises:
a rotor interface configured to engage an interface of a hub rotor disposed aft of the bladed rotor, the rotor interface comprising a radially inward surface, wherein a diameter extending between the center axis of the gas turbine engine and the radially inward surface along an axial span of the rotor interface is constant; and
a relief zone comprising a multi-curved curvilinear geometry radially overlapping with the radially inward surface and located radially outward of the radially inward surface to decrease a thickness of the bladed rotor and form a narrowed neck of the bladed rotor at the multi-curved curvilinear geometry, the multi-curved curvilinear geometry comprising a first surface having a first radius and a second surface having a second radius, wherein the first surface and the second surface meet at a peak defined where the first radius and the second radius intersect;
wherein the rotor interface and the interface of the hub rotor are configured to provide a sliding surface over which the bladed rotor and the hub rotor at least one of slide or rotate with respect to one another.

2. The bladed rotor of claim 1 , wherein an axial dimension of the axial span is between about 1% and 99% of an axial width of the rotor interface.

3. The bladed rotor of claim 1 , wherein an axial dimension of the axial span is between about 5% and 50% of an axial width of the rotor interface.

4. A hub rotor for a gas turbine engine, the gas turbine engine comprising a center axis extending from forward to aft, wherein the hub rotor comprises:
a hub interface configured to engage an interface of a bladed rotor disposed forward of the hub rotor, the hub interface comprising a radially outward surface; and
a relief zone comprising at least one of a multi-curved curvilinear surface radially overlapping with the radially outward surface and creating a peak at an intersection of a first surface having a first radius and a second surface having a second radius wherein the first surface and the second surface meet at the peak, a slot, a pocket, an extrude cut, and a trench located radially inward of the radially outward surface to decrease a thickness of the bladed rotor and form a narrowed neck of the bladed rotor;
wherein the hub interface and the interface of the bladed rotor are configured to provide a sliding surface over which the hub rotor and the bladed rotor at least one of slide or rotate with respect to one another.

5. The hub rotor of claim 4 , wherein an axial dimension of the relief zone is between about 1% and 55% of an axial width of the hub interface.

6. A bladed rotor assembly for a gas turbine engine, comprising:
a bladed rotor comprising a rotor interface comprising a radially inward surface and a first relief zone having a multi-curved curvilinear geometry radially overlapping with the radially inward surface and located radially outward of the radially inward surface to decrease a thickness of the bladed rotor and form a narrowed neck of the bladed rotor at the multi-curved curvilinear geometry, the multi-curved curvilinear geometry comprising a first surface having a first radius and a second surface having a second radius, wherein the first surface and the second surface meet at a peak defined where the first radius and the second radius intersect; and
a hub rotor comprising a hub interface comprising a radially outward surface and a second relief zone having at least one of the multi-curved curvilinear surface, a slot, a pocket, an extrude cut, and a trench located radially inward of the radially outward surface to decrease a thickness of the bladed rotor and form a narrowed neck of the bladed rotor;
wherein the rotor interface and the hub interface are configured to provide a sliding surface over which the bladed rotor and the hub rotor at least one of slide or rotate with respect to one another.

7. The bladed rotor assembly of claim 6 , wherein the radially inward surface further comprises a constant diameter zone, wherein a diameter along a width of the constant diameter zone is constant.

Assignees

• United Technologies Corp
• Pratt & Whitney

Inventors

• Wilber John E
• Reilly Bernard J
• Palitsch Jeffrey M
• Patel Rimal
• Carmichael Jesse T
• Quinn Ryan H

Classifications

• F05D2260/941

  particularly aimed at mechanical or thermal stress reduction · CPC title

• F01D5/026

  Shaft to shaft connections · CPC title

• F01D5/025

  Fixing blade carrying members on shafts (attachment of a member on a shaft in general F16D1/06; for non-positive displacement pumps F04D29/00) · CPC title

• F04D29/083

  especially adapted for elastic fluid pumps · CPC title

• F01D5/02

  Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) · CPC title