# US 10,480,333 B2 · Turbine blade including balanced mateface condition

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- Number: US 10,480,333 B2
- Document ID: US10480333B2
- Status: Granted
- Kind: B2
- Application number: 15/607,998
- Filed: 2017-05-30
- Published: 2018-12-06
- Granted: 2019-11-19
- Earliest claimed: 2017-05-30
- Assignees: United Technologies Corporation
- Applicants: United Technologies Corporation
- Inventors: Evan P. Molony; Carey Clum; Wolfgang Balzer
- Web page: https://patentgrep.com/patent/US10480333B2

## CPC

- F01D 5/3015: {with side plates}
- F01D 5/141: {Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147)}
- F01D 5/143: {Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour}
- 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 9/042: {fixing blades to stators (fixing stator-rings in the casing or to each other F01D25/246)}
- F01D 11/006: {Sealing the gap between rotor blades or blades and rotor}
- F01D 5/145: {Means for influencing boundary layers or secondary circulations (for compressors F04D29/68)}
- F01D 9/041: {using blades (F01D5/148 takes precedence)}
- F05B 2240/301: Cross-section characteristics
- F05B 2240/80: Platforms for stationary or moving blades
- F05D 2240/11: Shroud seal segments
- F05D 2240/80: Platforms for stationary or moving blades
- 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)
- F05B: INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- 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 for a gas powered turbine includes a platform having a leading edge and a trailing edge. The leading edge is connected to the trailing edge by a suction side mateface and by a pressure side mateface. A blade extends outward from the platform. The blade has a foil shaped cross section and a suction side of the blade faces the suction side mateface and a pressure side of the blade faces the pressure side mateface. A radial height of the suction side mateface is different from a radial height of the pressure side mateface at a first axial position.

## Claims

### Claim 1

A blade for a gas powered turbine comprising:
a platform having a leading edge and a trailing edge, the leading edge being connected to the trailing edge by a suction side mateface and by a pressure side mateface;
a blade extending outward from said platform, the blade having an airfoil shaped cross section, wherein a suction side of the blade faces the suction side mateface, and a pressure side of the blade faces the pressure side mateface; and
a radial height of the suction side mateface is different from a radial height of the pressure side mateface at a first axial position, and wherein a difference between the radial height of the suction side mateface and the radial height of the pressure side mateface at the first axial position is an ideal disparity for a balanced manufacturing range at the first axial position.

### Claim 2 (depends on 1)

The blade of claim 1, wherein the ideal balanced manufacturing range is a radial height difference configured to balance negative waterfall effects and negative damming effects that arise due to manufacturing variability.

### Claim 3 (depends on 1)

The blade of claim 1, wherein the ideal disparity is in a range of disparities that generate a waterfall effect in an assembled rotor system.

### Claim 4 (depends on 1)

The blade of claim 1, wherein the platform further comprises a contoured radially outward facing surface, and wherein at least one contour of the contoured radially outward facing surface extends to one of said suction side mateface and said pressure side mateface.

### Claim 5 (depends on 4)

The blade of claim 4, wherein the radial height of the suction side mateface is different from the radial height of the pressure side mateface at a second axial position, and wherein the difference at the second axial position is distinct from the difference at the first axial position.

### Claim 6 (depends on 5)

The blade of claim 5, wherein the radial height of the suction side mateface is the same as the radial height of the pressure side mateface at a third axial position.

### Claim 7 (depends on 6)

The blade of claim 6, wherein the third axial position is between the first axial position and the second axial position.

### Claim 8 (depends on 1)

The blade of claim 1, wherein the blade is a rotor blade for one of a turbine based aircraft engine and a land based turbine.

### Claim 9

A gaspath component for a gas powered turbine comprising:
a platform having a leading edge and a trailing edge, the leading edge being connected to the trailing edge by a first side mateface and by a second side mateface circumferentially opposite the first side mateface; and
a radial height of the first side mateface is different from a radial height of the second side mateface at a first axial position, wherein a difference between the radial height of the first side mateface and the radial height of the second side mateface at the first axial position is an ideal disparity for a balanced manufacturing range at the first axial position, and the ideal balanced manufacturing range is a radial height difference configured to balance negative waterfall effects and negative damming effects that arise due to manufacturing variability.

### Claim 10 (depends on 9)

The gaspath component of claim 9, wherein the ideal disparity is in a range of disparities that generate a waterfall effect in an assembled rotor system.

### Claim 11 (depends on 9)

The gaspath component of claim 9, wherein the platform further comprises a contoured radially facing surface, and wherein at least one contour of the contoured radially facing surface extends to one of said first side mateface and said second side mateface.

### Claim 12 (depends on 11)

The gaspath component of claim 11, wherein the radial height of the first side mateface is different from the radial height of the second side mateface at a second axial position, and wherein the difference at the second axial position is distinct from the difference at the first axial position.

### Claim 13 (depends on 12)

The gaspath component of claim 12, wherein the radial height of the first side mateface is the same as the radial height of the second side mateface at a third axial position.

### Claim 14

A gas powered turbine comprising:
a compressor section;
a combustor section fluidly connected to the compressor section;
a turbine section fluidly connected to the combustor section;
at least one of said compressor section and said turbine section including a rotor stage comprised of a plurality of rotor blades, wherein each of said rotor blades includes a blade extending outward from a platform, the blade having an airfoil shaped cross section, wherein a suction side of the blade faces a suction side mateface of the platform, and a pressure side of the blade faces a pressure side mateface of the platform and a radial height of the suction side mateface is different from a radial height of the pressure side mateface at a first axial position, such that a radial height disparity exists across a mateface gap at any given axial position wherein the radial height disparity is an ideal disparity for a balanced manufacturing range at a first axial position.

### Claim 15 (depends on 14)

The gas powered turbine of claim 14, wherein the mateface gap is a gap disposed between a suction side mateface of a first platform and a pressure side mateface of a second platform circumferentially adjacent to the first platform.

### Claim 16 (depends on 14)

The gas powered turbine of claim 14, wherein the ideal balanced manufacturing range is a radial height difference configured to balance negative waterfall effects and negative damming effects that arise due to manufacturing variability.