Hydraulic device for emergency starting a turbine engine, propulsion system of a multi-engine helicopter provided with one such device, and corresponding helicopter

Patent metadata

Field	Value
Publication number	US-10422285-B2
Application number	US-201515125105-A
Country	US
Kind code	B2
Filing date	Mar 20, 2015
Priority date	Mar 27, 2014
Publication date	Sep 24, 2019
Grant date	Sep 24, 2019

Abstract

Emergency start-up device for a turboshaft engine of a helicopter, comprising: a hydraulic motor which is mechanically connected to said turboshaft engine; a hydropneumatic store which is connected to said hydraulic motor by a hydraulic circuit for supplying pressurized liquid to said hydraulic motor; and a hydraulic valve which has controlled quick opening, arranged on the hydraulic circuit between said store and said hydraulic motor, and is suitable for being placed on command at least in an open position in which the liquid can supply said hydraulic motor, or in a closed position in which said hydraulic motor is no longer supplied with pressurized liquid.

First claim

The invention claimed is:

1. An emergency start-up device for a turboshaft engine of a helicopter, comprising:
a hydraulic motor configured to be mechanically connected to said turboshaft engine and is configured to set into rotation said engine to facilitate the start-up thereof;
a hydropneumatic store connected to said hydraulic motor by a hydraulic circuit, the hydropneumatic store configured to supply pressurized liquid to said hydraulic motor;
a hydraulic valve being connected between said hydropneumatic store and said hydraulic motor, wherein the hydraulic valve is controllable between at least an open position in which the liquid can supply said hydraulic motor for facilitating a start-up of said turboshaft engine when the device is used with said turboshaft engine and a closed position in which said hydraulic motor is no longer supplied with pressurized liquid; and
a reservoir configured for recovering liquid, the reservoir being connected to said hydraulic motor by a purge valve;
wherein said hydraulic motor comprises a propshaft configured to be mechanically connected to a gearbox shaft of an accessory gearbox of said turboshaft engine by meshing means comprising at least one free wheel supported by said propshaft, wherein said meshing means further comprise:
a first meshing stage comprising said propshaft supporting a main pinion mounted on said free wheel and a first pumping pinion;
a second meshing stage comprising said gearbox shaft supporting a main pinion meshed with said main pinion from said first meshing stage, and a second pumping pinion; and
an intermediate meshing stage comprising an intermediate shaft supporting a connection pinion movable between an engaged position in which the connection pinion is engaged together with said first and second pumping pinions from the first and second stages, and a disengaged position in which the connection pinion does not interfere with said pumping pinions from the first and second stages.

2. A propulsion system for a multi-engine helicopter comprising turboshaft engines which are suitable for being connected to a power transmission gearbox, comprising:
at least one hybrid turboshaft engine among said turboshaft engines, said at least one hybrid turboshaft engine being capable of operating in at least one standby regime during a stabilized flight of the helicopter, the other turboshaft engines operating only during this stabilized flight; and
at least one emergency start-up device for the emergency start-up of the at least one hybrid turboshaft engine, said at least one device configured to transfer said at least one hybrid turboshaft engine out of said standby regime and reach a rated regime in which it supplies mechanical power to said power transmission gearbox, said emergency start-up device comprising:
a hydraulic motor configured to be mechanically connected to said hybrid turboshaft engine and configured to set into rotation said hybrid turboshaft engine to facilitate the start-up thereof;
a hydropneumatic store connected to said hydraulic motor by a hydraulic circuit, the hydropneumatic store configured to supply pressurized liquid to said hydraulic motor;
a hydraulic valve being connected between said hydropneumatic store and said hydraulic motor, wherein the hydraulic valve is controllable between at least an open position in which the liquid can supply said hydraulic motor for facilitating a start-up of said hybrid turboshaft engine when the device is used with said hybrid turboshaft engine and a closed position in which said hydraulic motor is no longer supplied with pressurized liquid; and
a reservoir configured for recovering liquid, the reservoir being connected to said hydraulic motor by a purge valve.

3. The system according to claim 2 , wherein said at least one hybrid turboshaft engine includes two turboshaft engines and wherein two emergency start-up devices are provided, each turboshaft engine of said two hybrid turboshaft engines being associated with an emergency start-up device.

4. The system according to claim 2 , wherein said at least one hybrid turboshaft engine includes two turboshaft engines and wherein a single emergency start-up device including two hydraulic motors is provided, each hydraulic motor connected to one of the hybrid turboshaft engines of said two hybrid turboshaft engines, respectively, said hydraulic valve being a three-way valve controlled to orient the fluid towards said hydraulic motor of the hybrid turboshaft engine to be restarted.

5. The system according to claim 2 , wherein said hydropneumatic store includes a bladder.

6. The system according to claim 2 , wherein said hydropneumatic store includes a membrane.

7. The system according to claim 2 , wherein said hydropneumatic store includes a piston.

8. The system according to claim 2 , wherein the hydropneumatic store includes a first compartment of variable volume having a gas stored therein and a second compartment of variable volume having a hydraulic liquid stored therein.

9. The system according to claim 2 , wherein the gas is selected from a group selected from nitrogen, helium, and argon.

10. The system according to claim 2 , wherein said hydropneumatic store is selected from the group consisting of a bladder-type store, a membrane-type store and a piston-type store.

11. The system according to claim 2 , wherein said hydraulic motor comprises a propshaft configured to be mechanically connected to a gearbox shaft of an accessory gearbox of said hybrid turboshaft engine by meshing means comprising at least one free wheel supported by said propshaft.

12. The system according to claim 11 , wherein said meshing means further comprise:
a first meshing stage comprising said propshaft supporting a main pinion mounted on said free wheel and a pumping pinion;
a second meshing stage comprising said gearbox shaft supporting a main pinion meshed with said main pinion from said first meshing stage, and a pumping pinion; and
an intermediate meshing stage comprising an intermediate shaft supporting a connection pinion movable between an engaged position in which it is engaged together with said pumping pinions from the first and second stages, and a disengaged position in which it does not interfere with said pumping pinions from the first and second stages.

13. The system according to claim 2 , wherein said hydraulic motor comprises a propshaft configured to be mechanically connected to a gearbox shaft of an accessory gearbox of said hybrid turboshaft engine by a transmission comprising at least one free wheel supported by said propshaft.

14. A helicopter comprising the propulsion system according to claim 2 .

Assignees

• Safran Helicopter Engines

Inventors

• Thiriet Romain
• Moine Bertrand
• Serghine Camel
• Porel François

Classifications

• F01D19/00 Primary

  Starting of machines or engines; Regulating, controlling, or safety means in connection therewith (warming-up before starting F01D25/10; turning or inching gear F01D25/34) · CPC title

• F02C7/275 Primary

  Mechanical drives · CPC title

• F05D2270/093

  of one engine in a multi-engine system · CPC title

• F05D2260/42

  Storage of energy · CPC title

• F02C6/14

  Gas-turbine plants having means for storing energy, e.g. for meeting peak loads · CPC title