# US 9,752,441 B2 · Gas turbine rotary blade with tip insert > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 9,752,441 B2 - Document ID: US9752441B2 - Status: Granted - Kind: B2 - Application number: 13/362,968 - Filed: 2012-01-31 - Published: 2013-08-01 - Granted: 2017-09-05 - Earliest claimed: 2012-01-31 - Assignees: United Technologies Corporation - Applicants: Gregory C. Hildebrand; James O. Hansen; Joseph Parkos, Jr.; Michael A. Weisse; Christopher J. Hertel; Jesse Meyer - Inventors: Gregory C. Hildebrand; James O. Hansen; Joseph Parkos, Jr.; Michael A. Weisse; Christopher J. Hertel; Jesse Meyer - Web page: https://patentgrep.com/patent/US9752441B2 ## CPC - F01D 5/20: Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)} - F01D 11/122: {with erodable or abradable material (blades having cutting or grinding tips F01D5/20)} - F05D 2220/36: specially adapted for the fan of turbofan engines - F05D 2240/307: related to the tip of a rotor blade - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A rotary blade is provided that includes a root, an airfoil, and a tip insert. The airfoil is attached to the root, and has a suction side surface, a pressure side surface, a leading edge, a trailing edge, a tip, and a slot disposed within the tip. The slot extends in a chordwise direction between the leading edge and trailing edge. The tip insert has a base end and a rub end. The base end of the tip insert is disposed within the slot. The rub end of the tip insert extends radially outward from the airfoil tip. ## Claims ### Claim 1 A rotary blade, comprising: a root, an airfoil attached to the root, wherein the airfoil has a suction side surface, a pressure side surface, a leading edge, a trailing edge, a tip, and a slot disposed within the tip, and wherein the slot extends in a chordwise direction between the leading edge and trailing edge; and a tip insert having a base end and a rub end, the tip insert configured as a unitary and uninterrupted body; wherein the base end of the tip insert is disposed within the slot, and the rub end of the tip insert extends radially outward from the airfoil tip; wherein the tip insert and the airfoil are discretely formed bodies; wherein the tip insert comprises metal and/or ceramic; and wherein the slot is disposed in the tip between the pressure side surface and the suction side surface of the airfoil; and wherein a portion of the slot extends to the pressure side surface of the rotary blade adjacent to the trailing edge of the blade. ### Claim 2 (depends on 1) The rotary blade of claim 1, wherein the slot extends all the way between the leading edge and the trailing edge. ### Claim 3 (depends on 1) The rotary blade of claim 1, further comprising a leading edge insert disposed at the leading edge of the rotary blade. ### Claim 4 (depends on 1) The rotary blade of claim 1, wherein the airfoil comprises aluminum, and the tip insert comprises anodized aluminum, titanium and/or ceramic. ### Claim 5 (depends on 1) The rotary blade of claim 1, wherein the slot is substantially rectangular-shaped. ### Claim 6 (depends on 1) The rotary blade of claim 1, wherein at least a portion of the slot is arcuately shaped. ### Claim 7 (depends on 1) The rotor blade of claim 1, wherein the tip insert is made of a material with a greater durability than a material from which the airfoil is made. ### Claim 8 A rotary blade, comprising: a root, an airfoil attached to the root, wherein the airfoil has a suction side surface, a pressure side surface, a leading edge, a trailing edge, a tip, and a slot disposed within the tip, and wherein the slot extends in a chordwise direction between the leading edge and trailing edge; a tip insert having a base end and a rub end, the tip insert configured as a unitary and uninterrupted body; and a leading edge insert disposed at the leading edge of the rotary blade; wherein the base end of the tip insert is disposed within the slot, and the rub end of the tip insert extends radially outward from the airfoil tip; wherein the tip insert and the airfoil are discretely formed bodies; wherein the tip insert comprises metal and/or ceramic; and wherein the leading edge insert extends chordwise along a first portion of the tip for a first distance, the tip insert extends chordwise along a second portion of the tip for a second distance, and a sum of the first distance and the second distance is equal to or greater than a chordlength of the airfoil tip. ### Claim 9 A rotary blade tip insert for a rotary blade having an airfoil that has a suction side surface, a pressure side surface, a leading edge, a trailing edge, a tip, and a slot disposed within the tip, wherein the slot extends in a chordwise direction between the leading edge and trailing edge, the tip insert comprising: a unitary and uninterrupted body having a width extending radially between an inner surface of a base end and an outer surface of a rub end, and a length extending between a forward end and an aft end; wherein the base end is configured to be received within the slot and the rub end is configured to extend radially outward from the airfoil tip; wherein the tip insert comprises metal and/or ceramic; wherein the tip insert is at least one of welded or brazed to the airfoil; wherein the slot is disposed in the tip between the pressure side surface and the suction side surface; and wherein a portion of the slot extends to the pressure side surface adjacent to the trailing edge. ### Claim 10 (depends on 9) The rotary blade tip insert of claim 9, wherein the length of the tip insert is substantially equal to the chordwise distance between the leading edge and the trailing edge of the airfoil. ### Claim 11 (depends on 9) The rotary blade tip insert of claim 9, wherein the tip insert comprises anodized aluminum, titanium and/or ceramic. ### Claim 12 (depends on 9) The rotary blade tip insert of claim 9, wherein a widthwise cross-section of the tip insert is substantially rectangular-shaped. ### Claim 13 (depends on 9) The rotary blade tip insert of claim 9, wherein at least a portion of a width-wise cross-section of the tip insert is arcuately shaped. ### Claim 14 A rotary blade assembly within a gas turbine engine, the assembly comprising: a plurality of rotary blades extending radially outwardly from a hub, each of the rotor blades having a tip insert and an airfoil that has a suction side surface, a pressure side surface, a leading edge, a trailing edge, a tip, and a slot disposed within the tip, wherein the slot extends in a chordwise direction between the leading edge and trailing edge, wherein the tip insert has a base end and a rub end, and wherein the base end of the tip insert is disposed within the slot, and the rub end of the tip insert extends radially outward from the airfoil tip; and a containment case disposed radially outside of the rotary blades and circumferentially surrounding the plurality of blades, wherein the containment case includes an abradable blade outer air seal; wherein the tip insert and the airfoil are discretely formed bodies; wherein the tip insert comprises metal and/or ceramic, and the tip insert is configured as an integrally formed body; wherein the tip insert is at least one of welded or brazed to the airfoil; wherein the slot is disposed in the tip between the pressure side surface and the suction side surface; and wherein a portion of the slot extends to the pressure side surface adjacent to the trailing edge. ### Claim 15 (depends on 14) The rotary blade assembly of claim 14, wherein the plurality of rotary blades are fan blades. ### Claim 16 (depends on 14) The rotary blade assembly of claim 14, wherein the airfoil comprises aluminum, and the tip insert comprises anodized aluminum, titanium and/or ceramic. ### Claim 17 (depends on 14) The rotary blade assembly of claim 14, wherein the slot in each of the plurality of rotary blades is at least partially arcuately shaped. ### Claim 18 (depends on 14) The rotary blade assembly of claim 14, wherein the plurality of rotary blades are compressor blades. ### Claim 19 (depends on 14) The rotary blade assembly of claim 14, wherein the plurality of rotary blades are turbine blades.