# US 8,770,931 B2 · Hybrid Ceramic Matrix Composite vane structures for a gas turbine engine

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- Number: US 8,770,931 B2
- Document ID: US8770931B2
- Status: Granted
- Kind: B2
- Application number: 13/116,144
- Filed: 2011-05-26
- Published: 2012-11-29
- Granted: 2014-07-08
- Earliest claimed: 2011-05-26
- Assignees: United Technologies Corporation
- Applicants: Ioannis Alvanos; Gabriel L. Suciu
- Inventors: Ioannis Alvanos; Gabriel L. Suciu
- Web page: https://patentgrep.com/patent/US8770931B2

## CPC

- F01D 5/284: {Selection of ceramic materials}
- C04B 37/001: {directly with other burned ceramic articles}
- F01D 5/282: {Selecting composite materials, e.g. blades with reinforcing filaments}
- F01D 9/041: {using blades (F01D5/148 takes precedence)}
- F01D 11/001: {for sealing space between stator blade and rotor}
- F01D 25/246: {Fastening of diaphragms or stator-rings}
- C04B 2237/38: Fiber or whisker reinforced
- C04B 2237/86: Joining of two substrates at their largest surfaces, one surface being complete joined and covered, the other surface not, e.g. a small plate joined at it's largest surface on top of a larger plate
- F05D 2300/6033: Ceramic matrix composites [CMC]
- Y10T 29/49321: Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
- Y10T 29/49323: Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- C04B: LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE {(roofing granules E04D7/005)}; CERAMICS (devitrified glass-ceramics C03C10/00); REFRACTORIES; TREATMENT OF NATURAL STONE
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION

## Abstract

A vane structure for a gas turbine engine includes a multiple of CMC airfoil sections integrated between a CMC outer ring and a metal alloy inner ring.

## Claims

### Claim 1

A vane structure for a gas turbine engine comprising:
a CMC outer ring;
a metal alloy inner ring; and
a multiple of CMC airfoil sections between said CMC outer ring and said metal alloy inner ring.

### Claim 2 (depends on 1)

The vane structure as recited in claim 1, wherein said multiple of CMC airfoil sections are within a Low Pressure Turbine.

### Claim 3 (depends on 1)

The vane structure as recited in claim 1, further comprising a splined interface which extends from said CMC outer ring.

### Claim 4 (depends on 1)

The vane structure as recited in claim 1, wherein said multiple of CMC airfoil sections are bonded to said CMC outer ring.

### Claim 5 (depends on 1)

The vane structure as recited in claim 1, wherein said metal alloy inner ring includes a key slot to receive said multiple of CMC airfoil sections individually.

### Claim 6 (depends on 1)

The vane structure as recited in claim 1, wherein said CMC outer ring includes a key slot to receive said multiple of CMC airfoil sections individually.

### Claim 7 (depends on 1)

The vane structure as recited in claim 1, wherein each of said multiple of CMC airfoil sections include an inner platform structure and an outer platform structure.

### Claim 8 (depends on 7)

The vane structure as recited in claim 7, wherein said inner platform structure provides a complementary geometry to abut each adjacent inner platform structure.

### Claim 9 (depends on 8)

The vane structure as recited in claim 8, wherein said metal alloy inner ring extends at least partially around said inner platform structure.

### Claim 10 (depends on 7)

The vane structure as recited in claim 7, wherein said outer platform structure provides a complementary geometry to abut each adjacent outer platform structure.

### Claim 11

A Low Pressure Turbine for a gas turbine engine comprising:
a CMC outer ring;
a metal alloy inner ring; and
a multiple of Low Pressure Turbine CMC airfoil sections between said CMC outer ring and said metal alloy inner ring.

### Claim 12 (depends on 11)

The Low Pressure Turbine as recited in claim 11, further comprising a low pressure turbine case, said CMC outer ring mounted to said low pressure turbine case through a splined interface.

### Claim 13 (depends on 12)

The Low Pressure Turbine as recited in claim 12, wherein said low pressure turbine case is manufactured of CMC.

### Claim 14 (depends on 12)

The Low Pressure Turbine as recited in claim 12, further comprising a support structure which extends radially inward from said low pressure turbine case.

### Claim 15

A method of assembling a vane structure for a gas turbine engine comprising:
inserting a multiple of CMC airfoil sections between a CMC outer ring and a metal alloy inner ring.

### Claim 16 (depends on 15)

The method as recited in claim 15, further comprising:
individually inserting the multiple of CMC airfoil sections through a key slot in the CMC outer ring.

### Claim 17 (depends on 15)

The method as recited in claim 15, further comprising:
bonding the multiple of CMC airfoil sections to the CMC outer ring.

### Claim 18 (depends on 15)

The method as recited in claim 15, further comprising:
individually inserting the multiple of CMC airfoil sections through a key slot in the metal alloy inner ring.

### Claim 19 (depends on 15)

The method as recited in claim 15, further comprising:
bending a portion of the metal alloy inner ring at least partially around a platform of the multiple of CMC airfoil sections.