# US 11,028,701 B2 · Structure for cooling turbine blade

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- Number: US 11,028,701 B2
- Document ID: US11028701B2
- Status: Granted
- Kind: B2
- Application number: 16/477,670
- Filed: 2017-12-27
- Published: 2019-11-28
- Granted: 2021-06-08
- Earliest claimed: 2017-01-18
- Assignees: Kawasaki Jukogyo Kabushiki Kaisha
- Applicants: Kawasaki Jukogyo Kabushiki Kaisha
- Inventors: Tomoko Tsuru; Katsuhiko Ishida
- Web page: https://patentgrep.com/patent/US11028701B2

## 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 5/187: {Convection cooling}
- F01D 5/18: Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades
- F01D 5/186: {Film cooling (F01D5/187 takes precedence)}
- F01D 5/188: {with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall}
- F01D 9/065: {Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26)}
- F01D 25/12: Cooling
- F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)}
- F05D 2260/201: by impingement of a fluid
- F05D 2260/221: Improvement of heat transfer
- F05D 2260/22141: using fins or ribs
- 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

A structure for cooling a turbine airfoil includes: a cooling passage formed between first and second airfoil walls; a lattice structure body formed by stacking a plurality of ribs so as to form a lattice pattern; a cooling medium discharge port provided at a downstream end portion of the cooling passage for discharging cooling medium to the outside; an exposed wall portion formed as a portion of the second airfoil wall extending beyond the cooling medium discharge port to the outside; and a flat surface portion formed in the cooling passage from an outlet of the lattice structure body to the cooling medium discharge port and at which the wall surfaces of the first and second airfoil walls are formed as flat surfaces.

## Claims

### Claim 1

A structure for cooling a turbine airfoil of a turbine driven by a high-temperature gas, the structure comprising:
a cooling passage formed between a first airfoil wall of the turbine airfoil that is curved so as to be concave relative to a passage for the high-temperature gas and a second airfoil wall of the turbine airfoil that is curved so as to be convex relative to the passage for the high-temperature gas;
a lattice structure body including a first rib set composed of a plurality of first ribs provided on a wall surface, of the first airfoil wall, that faces the cooling passage, and a second rib set composed of a plurality of second ribs provided on a wall surface, of the second airfoil wall, that faces the cooling passage, the second rib set being stacked on the first rib set so as to form a lattice pattern;
a cooling medium discharge port provided at a downstream end portion of the cooling passage and configured to discharge the cooling medium within the cooling passage to the outside;
an exposed wall portion in the form of a portion of the second airfoil wall extending beyond the cooling medium discharge port to the outside; and
a flat surface portion that is a portion of the cooling passage from an outlet of the lattice structure body to the cooling medium discharge port and at which the wall surface of the first airfoil wall and the wall surface of the second airfoil wall are formed as flat surfaces,
wherein the flat surface portion has a length within a range of not less than 1 time and not greater than 5 times of a height of the outlet of the lattice structure body.

### Claim 2 (depends on 1)

The structure for cooling the turbine airfoil as claimed in claim 1, wherein a movement direction of the cooling medium is a direction along a chord of the turbine airfoil, and a plurality of the lattice structure bodies are disposed so as to be juxtaposed to each other in a height direction of the turbine airfoil with a partition body interposed therebetween.