# US 9,039,382 B2 · Blade skirt > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 9,039,382 B2 - Document ID: US9039382B2 - Status: Granted - Kind: B2 - Application number: 13/306,413 - Filed: 2011-11-29 - Published: 2013-05-30 - Granted: 2015-05-26 - Earliest claimed: 2011-11-29 - Assignees: General Electric Company - Applicants: David Scott Stapleton - Inventors: David Scott Stapleton - Web page: https://patentgrep.com/patent/US9039382B2 ## CPC - F01D 5/147: {Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18)} - F01D 5/143: {Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour} - F01D 5/30: Fixing blades to rotors; Blade roots {; Blade spacers} - F01D 5/3015: {with side plates} - F05D 2240/80: Platforms for stationary or moving blades - F05D 2250/70: Shape - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - 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 - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A blade of a gas turbine engine is provided having an airfoil, a platform, a shank, a dovetail, and a skirt. The airfoil may extend distally from the platform, and the shank may extend proximally from the platform. The dovetail may also be provided to extend proximally from the shank. The skirt may be disposed on an aft side of the shank and may extend from the shank in a direction at least partially axially aft from the shank. ## Claims ### Claim 1 A gas turbine engine blade comprising: a proximal end and a radially opposite distal end, and a forward side and an axially opposite aft side; an airfoil, a platform, a shank, and a dovetail; wherein said airfoil extends distally from said platform and terminates at said distal end, said shank extends proximally from said platform, and said dovetail extends proximally from said shank and terminates at said proximal end; a skirt disposed at least partially on an aft side of said shank and extending at least partially from said shank in a direction that is at least partially axially aft of said shank; wherein said skirt includes a skirt radius which serves as a transitioning surface between a proximal surface of said skirt and an aft surface of said shank and also between said aft surface of said shank and a lateral side of said shank. ### Claim 2 (depends on 1) The gas turbine engine blade of claim 1, wherein said skirt extends from said shank in a direction at least partially radially toward said proximal end. ### Claim 3 (depends on 1) The gas turbine engine blade of claim 1, wherein said skirt has a first skirt surface that faces axially toward said forward side and also faces radially toward said proximal end. ### Claim 4 (depends on 3) The gas turbine engine blade of claim 3, wherein said first skirt surface is disposed on a plane that is at an angle relative to said aft surface of said shank. ### Claim 5 (depends on 3) The gas turbine engine blade of claim 3, wherein said first skirt surface and said aft surface of said shank have a skirt radius disposed therebetween. ### Claim 6 (depends on 1) The gas turbine engine blade of claim 1 wherein said lateral side is a first lateral side and further comprising a laterally opposed second lateral side, wherein said skirt extends laterally from said first lateral side to said second lateral side. ### Claim 7 (depends on 1) The gas turbine engine blade of claim 1, wherein said skirt has an end portion extended away from and proud of said shank and uninterrupted across a lateral dimension of said skirt. ### Claim 8 (depends on 1) The gas turbine engine blade of claim 1, wherein said skirt has an end point at its radially proximal extreme that is disposed radially distally of a radially distal extreme of said dovetail. ### Claim 9 A gas turbine engine blade comprising: a proximal end and a radially opposite distal end, and a forward side and an axially opposed aft side; an airfoil, a platform, a shank, and a dovetail; wherein said airfoil extends distally from said platform and terminates at said distal end, said shank extends proximally from said platform, and said dovetail extends proximally from said shank and terminates at said proximal end; a skirt disposed on said aft side and at least partially extending from said aft side axially proud of an axially aft side surface of said shank; wherein said skirt includes a skirt radius which serves as a transitioning surface between a proximal surface of said skirt and said axially aft side surface of said shank and also between said axially aft side surface of said shank and a lateral side of said shank. ### Claim 10 (depends on 9) The gas turbine engine blade of claim 9, wherein said skirt extends from said aft side in a direction at least partially radially toward said proximal end. ### Claim 11 (depends on 9) The gas turbine engine blade of claim 9, wherein said skirt has a first skirt surface facing axially toward said forward side and facing radially toward said proximal end. ### Claim 12 (depends on 11) The gas turbine engine blade of claim 11, wherein said first skirt surface extends from said aft side at an angle from said axially aft side surface of said shank. ### Claim 13 (depends on 11) The gas turbine engine blade of claim 11, wherein said first skirt surface and said axially aft side surface of said shank have said skirt radius therebetween. ### Claim 14 (depends on 9) The gas turbine engine blade of claim 9 wherein said lateral side is a first lateral side and further comprising a laterally opposed second lateral side, wherein said skirt extends laterally from said first lateral side to said second lateral side generally uninterrupted. ### Claim 15 (depends on 9) The gas turbine engine blade of claim 9, wherein said skirt has an end point at its radially proximal extreme that is disposed radially distally of a radially distally extreme of said dovetail. ### Claim 16 (depends on 9) The gas turbine engine blade of claim 9, wherein said skirt extends from said shank. ### Claim 17 (depends on 9) The gas turbine engine blade of claim 9, wherein said skirt extends from said platform. ### Claim 18 A blade for a gas turbine engine comprising: a forward end and an axially opposed aft end along a longitudinal axis, and radial axes extending from and perpendicular to said longitudinal axis, each of said radial axes having a proximal end at said longitudinal axis and a radially opposed distal end; an airfoil, a platform, a shank, a dovetail, and a skirt; wherein said airfoil extends radially distally from said platform along one of said radial axes, said shank extends radially proximally from said platform along one of said radial axes, and said dovetail extends radially proximally from said shank along one of said radial axes; said skirt extending at least partially axially aft from said shank; wherein said skirt includes a skirt radius which serves as a transitioning surface between a proximal surface of said skirt and an aft surface of said shank and also between said aft surface of said shank and a lateral side of said shank.