# US 10,767,564 B2 · Air turbine starter with automated variable inlet vanes

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- Number: US 10,767,564 B2
- Document ID: US10767564B2
- Status: Granted
- Kind: B2
- Application number: 15/461,587
- Filed: 2017-03-17
- Published: 2018-09-20
- Granted: 2020-09-08
- Earliest claimed: 2017-03-17
- Assignees: Hamilton Sunstrand Corporation
- Applicants: Hamilton Sundstrand Corporation
- Inventors: Myles R. Kelly; James S. Elder
- Web page: https://patentgrep.com/patent/US10767564B2

## CPC

- F02C 7/277: the starter being a {separate} turbine
- F01D 9/041: {using blades (F01D5/148 takes precedence)}
- F01D 17/06: responsive to speed
- F01D 17/162: {for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence)}
- F01D 25/34: Turning or inching gear
- F02C 7/32: Arrangement, mounting, or driving, of auxiliaries
- F05D 2220/32: in gas turbines
- F05D 2240/128: Nozzles
- F05D 2260/85: Starting
- F05D 2270/304: Spool rotational speed
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- 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)
- 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

According to one embodiment, an air turbine starter is provided. The air turbine starter comprising: a turbine wheel including a hub integrally attached to a turbine rotor shaft and a plurality of turbine blades extending radially outward from the hub; an inlet housing at least partially surrounding the turbine wheel; a nozzle located upstream from the turbine wheel and contained within the inlet housing defining an inlet flowpath between the nozzle and the inlet housing, the inlet flowpath directs air flow into the turbine blades; and a plurality of turbine vanes rotatably connected to the nozzle, each turbine vane extending radially from the nozzle into the inlet flowpath towards the inlet housing; wherein the plurality of turbine vanes are operable to adjust air flow through the inlet flowpath by rotating each turbine vane.

## Claims

### Claim 1

An air turbine starter comprising:
a turbine wheel including a hub integrally attached to a turbine rotor shaft and a plurality of turbine blades extending radially outward from the hub;
an inlet housing at least partially surrounding the turbine wheel;
a nozzle located upstream from the turbine wheel and contained within the inlet housing defining an inlet flowpath between the nozzle and the inlet housing, the inlet flowpath directs air flow into the turbine blades;
a plurality of turbine vanes rotatably connected to the nozzle, each turbine vane extending radially from the nozzle into the inlet flowpath towards the inlet housing,
wherein the plurality of turbine vanes are operable to adjust air flow through the inlet flowpath by rotating each turbine vane, and
wherein each of the plurality of turbine vanes can be rotated to any selected angle in between a fully closed angle and a fully open angle, the selected angle is equal to zero degrees when at the fully open angle and the selected angle is equal to 90 degrees when at the fully closed angle,
a sync-ring operably connected to each turbine vane, wherein the sync-ring in operation rotates each turbine vane when the sync-ring moves,
an actuator operably connected to the sync-ring, wherein the actuator in operation moves the sync-ring;
a controller in communication with the actuator, wherein the controller is configured to operate the actuator in response to turbine blade airflow requirements of the air turbine starter, and
a speed sensor in communication with the controller, wherein the speed sensor in operation detects an angular velocity of the turbine rotor shaft,
wherein the controller is configured to determine the turbine blade airflow requirements of the air turbine starter to mitigate a bowed rotor condition of a gas turbine engine operably connected to the air turbine starter in response to an angular velocity of the gas turbine engine, an angular velocity of the turbine rotor shaft, and a pressure upstream of the air turbine starter, and
wherein the controller is further configured to operate the actuator in response to the determined turbine blade airflow requirements of the air turbine starter to mitigate the bowed rotor condition.

### Claim 2 (depends on 1)

The air turbine starter of claim 1, wherein:
the actuator is at least one of a pneumatic actuator, an electric actuator, or a hydraulic actuator.

### Claim 3 (depends on 1)

The air turbine starter of claim 1, wherein:
the speed sensor is located on the turbine rotor shaft.

### Claim 4

A method of assembling an air turbine starter comprising:
obtaining an inlet housing;
inserting a turbine wheel into the inlet housing, such that the inlet housing at least partially surrounds the turbine wheel, the turbine wheel including a hub integrally attached to a turbine rotor shaft and a plurality of turbine blades extending radially outward from the hub;
rotatably connecting a plurality of turbine vanes on to a nozzle, the plurality of turbine vanes extending radially outward from the nozzle;
inserting the nozzle into the inlet housing and upstream from the turbine wheel, the inlet housing defining an inlet flowpath between the nozzle and the inlet housing, the inlet flowpath configured to direct air flow into the plurality of turbine blades;
operably connecting a sync-ring to each of the plurality of turbine vanes, wherein the sync-ring in operation rotates each of the plurality of turbine vanes when the sync-ring moves, and
operably connecting an actuator to the sync-ring, wherein the actuator in operation moves the sync-ring,
electronically connecting a controller to the actuator, and
electronically connecting a speed sensor to the controller, wherein the speed sensor in operation detects the angular velocity of the turbine rotor shaft,
wherein the plurality of turbine vanes extend radially outward from the nozzle into the inlet flowpath towards the inlet housing and the plurality of turbine vanes are rotatable to adjust air flow through the inlet flowpath,
wherein each of the plurality of turbine vanes can be rotated to any selected angle in between a fully closed angle and a fully open angle, the fully open angle being equal to zero degrees and the fully closed angle being equal to 90 degrees, and
wherein the controller is configured to determine turbine blade airflow requirements of the air turbine starter to mitigate a bowed rotor condition of a gas turbine engine operably connected to the air turbine starter in response to an angular velocity of the gas turbine engine, an angular velocity of the turbine rotor shaft, and a pressure upstream of the air turbine starter, and
wherein the controller is further configured to operate the actuator in response to the determined turbine blade airflow requirements of the air turbine starter to mitigate the bowed rotor condition.

### Claim 5 (depends on 4)

The method of claim 4, wherein:
the actuator is at least one of a pneumatic actuator, an electric actuator or a hydraulic actuator.

### Claim 6 (depends on 4)

The method of claim 4, wherein:
the speed sensor is located on the turbine rotor shaft.