# US 10,480,532 B2 · Compressor stator vane, axial flow compressor, and gas turbine

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- Number: US 10,480,532 B2
- Document ID: US10480532B2
- Status: Granted
- Kind: B2
- Application number: 15/379,935
- Filed: 2016-12-15
- Published: 2017-04-06
- Granted: 2019-11-19
- Earliest claimed: 2014-08-12
- Assignees: IHI Corporation
- Applicants: IHI Corporation
- Inventors: Guillaume Pallot; Dai Kato
- Web page: https://patentgrep.com/patent/US10480532B2

## CPC

- F04D 29/542: {Bladed diffusers (fixing blades to stators F01D9/042)}
- F01D 9/041: {using blades (F01D5/148 takes precedence)}
- F02C 3/04: having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16)
- F04D 19/02: Multi-stage pumps
- F04D 29/321: {for axial flow compressors}
- F04D 29/544: {Blade shapes}
- 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 5/145: {Means for influencing boundary layers or secondary circulations (for compressors F04D29/68)}
- 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)}
- F04D 29/324: {Blades}
- F05D 2220/32: in gas turbines
- F05D 2240/35: Combustors or associated equipment
- F05D 2300/10: Metals, alloys or intermetallic compounds
- F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02)
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS

## Abstract

Within a compressor case, a plurality of stages of high-pressure compressor stators are disposed alternately with a plurality of stages of high-pressure compressor rotors along an axial direction. Each stage of the high-pressure compressor stators includes a plurality of compressor stator vanes. Each of the compressor stator vanes has, on a camber line, a camber reference point in which (θ−θe)/θk is 50% (θ, θe and θk represents a metal angle, an exit metal angle and a camber angle, respectively). In a vane-shaped cross-section, a distance from a leading edge to the camber reference point is set to a 26-38% chord.

## Claims

### Claim 1

A compressor stator vane for an axial flow compressor comprising:
a vane-shaped cross-section provided from a first side of the compressor stator vane to a second side of the compressor stator vane in a radial direction, the vane-shaped cross-section having, on a camber line, a camber reference point in which a ratio of an angle obtained by subtracting an exit metal angle from a metal angle to a camber angle is 50%, wherein
a distance from a leading edge to the camber reference point is set to a 26-38% chord,
the metal angle refers to an angle formed by a tangential direction of the camber line and an axial direction at an arbitrary position on the camber line,
the camber angle refers to an angle obtained by adding an entrance metal angle to the exit metal angle,
the entrance metal angle refers to an angle formed by the tangential direction of the camber line and the axial direction at an leading edge of the compressor stator vane, and
the exit metal angle refers to an angle formed by the tangential direction of the camber line and the axial direction at a trailing edge of the compressor stator vane.

### Claim 2

An axial flow compressor that compresses a fluid along an axial direction, the axial flow compressor comprising:
a cylindrical compressor case inside which an annular main flow path for circulating the fluid along the axial direction is formed;
a plurality of stages of compressor rotors that are rotatably provided within the compressor case along the axial direction and that include: a compressor disc whose outer circumferential surface constitutes a part of a wall surface of the main flow path on an inner side in a radial direction and which can be rotated; and a plurality of compressor rotor blades which are provided at intervals on the outer circumferential surface of the compressor disc along a circumferential direction thereof and which are located within the main flow path; and
a plurality of stages of compressor stators which are disposed alternately with the plurality of stages of compressor rotors within the compressor case along the axial direction and which include a plurality of compressor stator vanes that are arranged at intervals within the main flow path in the circumferential direction thereof and that rectify a flow of the fluid,
wherein each of the compressor stator vanes of at least any stage of the compressor stator among the plurality of stages of compressor stators has a vane-shaped cross-section provided from a first side of the compressor stator vane to a second side of the compressor stator vane in a radial direction,
wherein the vane-shaped cross-section has, on a camber line, a camber reference point in which a ratio of an angle obtained by subtracting an exit metal angle from a metal angle to a camber angle is 50%, and a distance from a leading edge to the camber reference point is set to a 26-38% chord,
wherein the metal angle refers to an angle formed by a tangential direction of the camber line and an axial direction at an arbitrary position on the camber line,
wherein the camber angle refers to an angle obtained by adding an entrance metal angle to the exit metal angle,
wherein the entrance metal angle refers to an angle formed by the tangential direction of the camber line and the axial direction at an leading edge of the compressor stator vane, and
wherein the exit metal angle refers to an angle formed by the tangential direction of the camber line and the axial direction at a trailing edge of the compressor stator vane.

### Claim 3 (depends on 2)

A gas turbine that exhausts a high-temperature and high-pressure combustion gas to thereby generate a propulsion force or a rotating force, the gas turbine comprising an axial flow compressor according to claim 2.