Apparatus and method for retaining bladed rotor disks of a jet engine
First Claim
1. An apparatus for retaining bladed rotor disks in a jet engine which includes an axial-flow compressor having a plurality of bladed rotor disks, with at least two bladed rotor disks at a compressor inlet side being designed as blisks where each blisk integrally combines a rotor disk and circumferentially distributed rotor blades;
- at least one turbine section; and
at least one shaft interconnecting the compressor and turbine section;
comprising;
at least one tie-rod, releasably retaining the blisks while the other rotor disks are firmly attached to each other separately and independently of the tie-rod.
1 Assignment
0 Petitions
Accused Products
Abstract
An apparatus (3) retains bladed rotor disks (4, 6, 9) of a jet engine which engine includes an axial-flow compressor with several bladed rotor disks (4, 6, 9), at least one turbine section, at least one shaft and at least one tie-rod (12, 47), with at least two bladed rotor disks at the compressor inlet side (2) being designed as blisks (6), each being a single component integrally combining a rotor disk and circumferentially distributed rotor blades (5). So that apparatus for the retention of blisks can easily be mounted and demounted, the blisks (6) are releasably retained via the tie-rod (12, 47) and the other rotor disks (4, 9) are firmly attached to each other separately and independently of the tie-rod (12, 47).
20 Citations
22 Claims
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1. An apparatus for retaining bladed rotor disks in a jet engine which includes an axial-flow compressor having a plurality of bladed rotor disks, with at least two bladed rotor disks at a compressor inlet side being designed as blisks where each blisk integrally combines a rotor disk and circumferentially distributed rotor blades;
- at least one turbine section; and
at least one shaft interconnecting the compressor and turbine section;
comprising;at least one tie-rod, releasably retaining the blisks while the other rotor disks are firmly attached to each other separately and independently of the tie-rod. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18)
- at least one turbine section; and
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19. A method for retaining bladed rotor disks in a jet engine which includes an axial-flow compressor having a plurality of bladed rotor disks, with at least two bladed rotor disks at a compressor inlet side being designed as blisks where each blisk integrally combines a rotor disk and circumferentially distributed rotor blades;
- at least one turbine section; and
at least one shaft interconnecting the compressor and turbine section;
comprising;releasably retaining the blisks with at least one tie rod; and separately and independently of the tie-rod, firmly attaching the other rotor disks to each other. - View Dependent Claims (20, 21, 22)
- at least one turbine section; and
Specification