{"stats":{"took":94,"total":38,"estimate":false,"maxScore":161.71986},"results":[{"_meta":{"score":161.71986},"copyright":{"thirdPartyPermissionsProduced":false,"disclosedToPublic":false,"containsIndication":false,"publisherPermissionOrRightsToDistribute":false,"belongsToUsGov":false,"determinationType":"GOV_PUBLIC_USE_PERMITTED","thirdPartyContentCondition":"NOT_SET","belongsToContractor":false,"disclosedInvention":false,"submissionId":19920004061,"containsThirdPartyMaterial":false,"belongsToPublisher":false,"id":"a265383a45d74e57a45e6081c4c82629","belongsToAuthors":false},"subjectCategories":["Spacecraft Propulsion And Power"],"exportControl":{"isExportControl":"NO","submissionId":19920004061,"ear":"NO","id":"0fac259374e34459bd9077012e46cb26","itar":"NO"},"distributionDate":"2019-06-25T00:00:00.0000000+00:00","otherReportNumbers":["NAS 1.15:103557","NASA-TM-103557","Report Number: NAS 1.15:103557","Report Number: NASA-TM-103557"],"title":"High-frequency data observations from space shuttle main engine low pressure fuel turbopump discharge duct flex joint tripod failure investigation","stiType":"TECHNICAL_MEMORANDUM","distribution":"PUBLIC","submittedDate":"2013-09-06T16:57:00.0000000+00:00","authorAffiliations":[{"sequence":0,"submissionId":19920004061,"meta":{"author":{"name":"Zoladz, T. F."},"organization":{"name":"NASA Marshall Space Flight Center","location":"Huntsville, AL, United States"}},"id":"e6bc61bda18840fd8c4178382aa36b17"},{"sequence":1,"submissionId":19920004061,"meta":{"author":{"name":"Farr, R. A."},"organization":{"name":"NASA Marshall Space Flight Center","location":"Huntsville, AL, United States"}},"id":"1dfa82b0cc794a2f93a2c82cebc80eb8"}],"stiTypeDetails":"Technical Memorandum (TM)","technicalReviewType":"TECHNICAL_REVIEW_TYPE_NONE","modified":"2025-08-31T18:39:21.7150190+00:00","id":19920004061,"legacyMeta":{"__type":"LegacyMetaIndex, StrivesApi.ServiceModel","accessionNumber":"92N13279"},"created":"2013-09-06T16:57:00.0000000+00:00","center":{"code":"CDMS","name":"Legacy CDMS","id":"092d6e0881874968859b972d39a888dc"},"onlyAbstract":false,"sensitiveInformation":2,"abstract":"Observations made by Marshall Space Flight Center (MSFC) engineers during their participation in the Space Shuttle Main Engine (SSME) low pressure fuel turbopump discharge duct flex joint tripod failure investigation are summarized. New signal processing techniques used by the Component Assessment Branch and the Induced Environments Branch during the failure investigation are described in detail. Moreover, nonlinear correlations between frequently encountered anomalous frequencies found in SSME dynamic data are discussed. A recommendation is made to continue low pressure fuel (LPF) duct testing through laboratory flow simulations and MSFC-managed technology test bed SSME testing.","isLessonsLearned":false,"disseminated":"DOCUMENT_AND_METADATA","publications":[{"submissionId":19920004061,"id":"83df23ae1eb64f1ead9a8c458e4580d4","publicationDate":"1991-12-01T00:00:00.0000000+00:00"}],"status":"CURATED","related":[],"downloads":[{"draft":false,"mimetype":"application/pdf","name":"19920004061.pdf","type":"STI","links":{"original":"/api/citations/19920004061/downloads/19920004061.pdf","pdf":"/api/citations/19920004061/downloads/19920004061.pdf","fulltext":"/api/citations/19920004061/downloads/19920004061.txt"}}],"downloadsAvailable":true,"index":"submissions-2026-05-21-04-55"},{"_meta":{"score":149.00351},"copyright":{"thirdPartyPermissionsProduced":false,"disclosedToPublic":false,"containsIndication":false,"publisherPermissionOrRightsToDistribute":false,"belongsToUsGov":false,"determinationType":"GOV_PUBLIC_USE_PERMITTED","thirdPartyContentCondition":"NOT_SET","belongsToContractor":false,"disclosedInvention":false,"submissionId":19870013332,"containsThirdPartyMaterial":false,"belongsToPublisher":false,"id":"7e4f001e1d5f43a4b7a4b97a1589d32a","belongsToAuthors":false},"subjectCategories":["Spacecraft Propulsion And Power"],"exportControl":{"isExportControl":"NO","submissionId":19870013332,"ear":"NO","id":"5d7cc49885e340adb09d71176f3ca91d","itar":"NO"},"distributionDate":"2019-06-24T00:00:00.0000000+00:00","otherReportNumbers":["NASA-CR-179079","BCD-SSME-TR-87-1","NAS 1.26:179079","Report Number: NASA-CR-179079","Report Number: BCD-SSME-TR-87-1","Report Number: NAS 1.26:179079"],"fundingNumbers":[{"number":"NASW-3737","submissionId":19870013332,"id":"bd697581c0ed4a289c46e4529608d840","type":"CONTRACT_GRANT"}],"title":"Studies and analyses of the space shuttle main engine: High-pressure oxidizer turbopump failure information propagation model","stiType":"CONTRACTOR_REPORT","distribution":"PUBLIC","submittedDate":"2013-09-05T09:30:00.0000000+00:00","authorAffiliations":[{"sequence":0,"submissionId":19870013332,"meta":{"author":{"name":"Glover, R. C."},"organization":{"name":"Battelle Columbus Labs.","location":"OH, United States"}},"id":"5ab699d8d6e64c67b61cf9f1b2ce5f5c"},{"sequence":1,"submissionId":19870013332,"meta":{"author":{"name":"Rudy, S. W."},"organization":{"name":"Battelle Columbus Labs.","location":"OH, United States"}},"id":"ed23cb75476e4365a3e96db6fd19daec"},{"sequence":2,"submissionId":19870013332,"meta":{"author":{"name":"Tischer, A. E."},"organization":{"name":"Battelle Columbus Labs.","location":"OH, United States"}},"id":"480fba3ac0e949e08c2794541c33da19"}],"stiTypeDetails":"Contractor Report (CR)","technicalReviewType":"TECHNICAL_REVIEW_TYPE_NONE","modified":"2025-08-31T18:39:21.7150190+00:00","id":19870013332,"legacyMeta":{"__type":"LegacyMetaIndex, StrivesApi.ServiceModel","accessionNumber":"87N22765"},"created":"2013-09-05T09:30:00.0000000+00:00","center":{"code":"CDMS","name":"Legacy CDMS","id":"092d6e0881874968859b972d39a888dc"},"onlyAbstract":false,"sensitiveInformation":2,"abstract":"The high-pressure oxidizer turbopump (HPOTP) failure information propagation model (FIPM) is presented. The text includes a brief discussion of the FIPM methodology and the various elements which comprise a model. Specific details of the HPOTP FIPM are described. Listings of all the HPOTP data records are included as appendices.","isLessonsLearned":false,"disseminated":"DOCUMENT_AND_METADATA","publications":[{"submissionId":19870013332,"id":"fa71937e1ff74be5b12633c2312b5e7d","publicationDate":"1987-04-20T00:00:00.0000000+00:00"}],"status":"CURATED","related":[],"downloads":[{"draft":false,"mimetype":"application/pdf","name":"19870013332.pdf","type":"STI","links":{"original":"/api/citations/19870013332/downloads/19870013332.pdf","pdf":"/api/citations/19870013332/downloads/19870013332.pdf","fulltext":"/api/citations/19870013332/downloads/19870013332.txt"}}],"downloadsAvailable":true,"index":"submissions-2026-05-21-04-55"},{"_meta":{"score":142.49525},"copyright":{"thirdPartyPermissionsProduced":false,"disclosedToPublic":false,"containsIndication":false,"publisherPermissionOrRightsToDistribute":false,"belongsToUsGov":false,"determinationType":"GOV_PUBLIC_USE_PERMITTED","thirdPartyContentCondition":"NOT_SET","belongsToContractor":false,"disclosedInvention":false,"submissionId":19900003334,"containsThirdPartyMaterial":false,"belongsToPublisher":false,"id":"04c196092d284ca1b0e9c4cd8c86c02a","belongsToAuthors":false},"subjectCategories":["Spacecraft Propulsion And Power"],"exportControl":{"isExportControl":"NO","submissionId":19900003334,"ear":"NO","id":"33fe2e18ac2b4280bc93ae1e289a37da","itar":"NO"},"distributionDate":"2019-06-24T00:00:00.0000000+00:00","otherReportNumbers":["NASA-CR-183671","NAS 1.26:183671","LMSC-HEC-TR-F268627","Report Number: NASA-CR-183671","Report Number: NAS 1.26:183671","Report Number: LMSC-HEC-TR-F268627"],"fundingNumbers":[{"number":"NAS8-37302","submissionId":19900003334,"id":"2ffe3ea13e624c83a092bff61a463283","type":"CONTRACT_GRANT"}],"title":"SSME structural dynamic model development","stiType":"CONTRACTOR_REPORT","distribution":"PUBLIC","submittedDate":"2013-09-06T14:56:00.0000000+00:00","authorAffiliations":[{"sequence":0,"submissionId":19900003334,"meta":{"author":{"name":"Foley, Michael J."},"organization":{"name":"Lockheed Missiles and Space Co.","location":"Huntsville, AL, United States"}},"id":"c1a014d3121b4c2fac386def7bb29361"}],"stiTypeDetails":"Contractor Report (CR)","technicalReviewType":"TECHNICAL_REVIEW_TYPE_NONE","modified":"2025-08-31T18:39:21.7150190+00:00","id":19900003334,"legacyMeta":{"__type":"LegacyMetaIndex, StrivesApi.ServiceModel","accessionNumber":"90N12650"},"created":"2013-09-06T14:56:00.0000000+00:00","center":{"code":"CDMS","name":"Legacy CDMS","id":"092d6e0881874968859b972d39a888dc"},"onlyAbstract":false,"sensitiveInformation":2,"abstract":"The high pressure fuel turbopump (HPFTP) is a major component of the Space Shuttle Main Engine (SSME) powerhead. The device is a three stage centrifugal pump that is directly driven by a two stage hot gas turbine. The purpose of the pump is to deliver fuel (liquid hydrogen) from the low pressure fuel turbopump (LPFTP) through the main fuel valve (MFV) to the thrust chamber coolant circuits. In doing so, the pump pressurizes the fuel from an inlet pressure of approximately 178 psi to a discharge pressure of over 6000 psi. At full power level (FPL), the pump rotates at a speed of over 37,000 rpm while generating approximately 77,000 horsepower. Obviously, a pump failure at these speeds and power levels could jeopardize the mission. Results are summarized for work in which the solutions obtained from analytical models of the fuel turbopump impellers are compared with the results obtained from dynamic tests.","isLessonsLearned":false,"disseminated":"DOCUMENT_AND_METADATA","publications":[{"submissionId":19900003334,"id":"f4039a23a0264ddd9243fd8bd0c95852","publicationDate":"1989-03-01T00:00:00.0000000+00:00"}],"status":"CURATED","related":[],"downloads":[{"draft":false,"mimetype":"application/pdf","name":"19900003334.pdf","type":"STI","links":{"original":"/api/citations/19900003334/downloads/19900003334.pdf","pdf":"/api/citations/19900003334/downloads/19900003334.pdf","fulltext":"/api/citations/19900003334/downloads/19900003334.txt"}}],"downloadsAvailable":true,"index":"submissions-2026-05-21-04-55"},{"_meta":{"score":140.96404},"copyright":{"thirdPartyPermissionsProduced":false,"disclosedToPublic":false,"containsIndication":false,"publisherPermissionOrRightsToDistribute":false,"belongsToUsGov":false,"determinationType":"OTHER","thirdPartyContentCondition":"NOT_SET","belongsToContractor":false,"disclosedInvention":false,"submissionId":19850057116,"containsThirdPartyMaterial":false,"belongsToPublisher":false,"id":"cef1483fa8e044868536b223580c409b","belongsToAuthors":false},"subjectCategories":["Spacecraft Propulsion And Power"],"exportControl":{"isExportControl":"NO","submissionId":19850057116,"ear":"NO","id":"3f8de93350c946e089fa3b4a4b725a71","itar":"NO"},"distributionDate":"2019-07-12T00:00:00.0000000+00:00","otherReportNumbers":["SAE PAPER 841619","Report Number: SAE PAPER 841619"],"fundingNumbers":[{"number":"NAS3-23349","submissionId":19850057116,"id":"f3a763f22c5c4d29ae7c0c815cdb9308","type":"CONTRACT_GRANT"}],"title":"Reusable rocket engine turbopump condition monitoring","stiType":"CONFERENCE_PAPER","distribution":"PUBLIC","submittedDate":"2013-08-12T11:32:00.0000000+00:00","authorAffiliations":[{"sequence":0,"submissionId":19850057116,"meta":{"author":{"name":"Hampson, M. E."},"organization":{"name":"Rockwell International Corp.","location":"Rocketdyne Div., Canoga Park, CA, United States"}},"id":"3e65e158c7ac4712907510662e6ca372"}],"stiTypeDetails":"Conference Paper","technicalReviewType":"TECHNICAL_REVIEW_TYPE_NONE","modified":"2025-08-31T18:39:21.7150190+00:00","id":19850057116,"legacyMeta":{"__type":"LegacyMetaIndex, StrivesApi.ServiceModel","accessionNumber":"85A39267"},"created":"2013-08-12T11:32:00.0000000+00:00","center":{"code":"CDMS","name":"Legacy CDMS","id":"092d6e0881874968859b972d39a888dc"},"onlyAbstract":false,"sensitiveInformation":2,"abstract":"Significant improvements in engine readiness with reductions in maintenance costs and turn-around times can be achieved with an engine condition monitoring systems (CMS). The CMS provides health status of critical engine components, without disassembly, through monitoring with advanced sensors. Engine failure reports over 35 years were categorized into 20 different modes of failure. Rotor bearings and turbine blades were determined to be the most critical in limiting turbopump life. Measurement technologies were matched to each of the failure modes identified. Three were selected to monitor the rotor bearings and turbine blades: the isotope wear detector and fiberoptic deflectometer (bearings), and the fiberoptic pyrometer (blades). Signal processing algorithms were evaluated for their ability to provide useful health data to maintenance personnel. Design modifications to the Space Shuttle Main Engine (SSME) high pressure turbopumps were developed to incorporate the sensors. Laboratory test fixtures have been designed for monitoring the rotor bearings and turbine blades in simulated turbopump operating conditions.","isLessonsLearned":false,"disseminated":"METADATA_ONLY","meetings":[{"submissionId":19850057116,"endDate":"1984-10-18T00:00:00.0000000+00:00","name":"Space systems technology","location":"Long Beach, CA","id":"194cb8aca37f4d5eba903a44809607e4","startDate":"1984-10-15T00:00:00.0000000+00:00"}],"publications":[{"submissionId":19850057116,"id":"fdfb7b145f9e4d60aef13ab9270da7b2","publicationDate":"1984-01-01T00:00:00.0000000+00:00"}],"status":"CURATED","related":[],"downloads":[],"downloadsAvailable":false,"index":"submissions-2026-05-21-04-55"},{"_meta":{"score":139.75847},"copyright":{"thirdPartyPermissionsProduced":false,"disclosedToPublic":false,"containsIndication":false,"publisherPermissionOrRightsToDistribute":false,"belongsToUsGov":false,"determinationType":"GOV_PUBLIC_USE_PERMITTED","thirdPartyContentCondition":"NOT_SET","belongsToContractor":false,"disclosedInvention":false,"submissionId":19840011321,"containsThirdPartyMaterial":false,"belongsToPublisher":false,"id":"f9fe56699239491894475eac6802bea1","belongsToAuthors":false},"subjectCategories":["Space Transportation"],"exportControl":{"isExportControl":"NO","submissionId":19840011321,"ear":"NO","id":"9014209837af4ff599c2560beacfa060","itar":"NO"},"distributionDate":"2019-06-24T00:00:00.0000000+00:00","otherReportNumbers":["RD-1-84","NAS 1.26:170987","NASA-CR-170987","Report Number: RD-1-84","Report Number: NAS 1.26:170987","Report Number: NASA-CR-170987"],"fundingNumbers":[{"number":"NAS8-34505","submissionId":19840011321,"id":"85ca84b576394d96907d4ebf9fe2d106","type":"CONTRACT_GRANT"}],"title":"Rotordynamic Characteristics of the HPOTP (High Pressure Oxygen Turbopump) of the SSME (Space Shuttle Main Engine)","stiType":"CONTRACTOR_REPORT","distribution":"PUBLIC","submittedDate":"2013-09-04T15:58:00.0000000+00:00","authorAffiliations":[{"sequence":0,"submissionId":19840011321,"meta":{"author":{"name":"Childs, D. W."},"organization":{"name":"Texas A&M Univ.","location":"College Station, TX, United States"}},"id":"859324b583fb4aa2a6f112be0b35fd8c"}],"stiTypeDetails":"Contractor Report (CR)","technicalReviewType":"TECHNICAL_REVIEW_TYPE_NONE","modified":"2025-08-31T18:39:21.7150190+00:00","id":19840011321,"legacyMeta":{"__type":"LegacyMetaIndex, StrivesApi.ServiceModel","accessionNumber":"84N19389"},"created":"2013-09-04T15:58:00.0000000+00:00","center":{"code":"CDMS","name":"Legacy CDMS","id":"092d6e0881874968859b972d39a888dc"},"onlyAbstract":false,"sensitiveInformation":2,"abstract":"Rotational stability of turbopump components in the space shuttle main engine was studied via analysis of component and structural dynamic models. Subsynchronous vibration caused unacceptable migration of the rotor/housing unit with unequal load sharing of the synchronous bearings that resulted in the failure of the High Pressure Oxygen Turbopump. Linear analysis shows that a shrouded inducer eliminates the second critical speed and the stability problem, a stiffened rotor improves the rotordynamic characteristics of the turbopump, and installing damper boost/impeller seals reduces bearing loads. Nonlinear analysis shows that by increasing the \"dead band' clearances, a marked reduction in peak bearing loads occurs.","isLessonsLearned":false,"disseminated":"DOCUMENT_AND_METADATA","publications":[{"submissionId":19840011321,"id":"28e1103170f64930a0e8908807eb3077","publicationDate":"1984-01-30T00:00:00.0000000+00:00"}],"status":"CURATED","related":[],"downloads":[{"draft":false,"mimetype":"application/pdf","name":"19840011321.pdf","type":"STI","links":{"original":"/api/citations/19840011321/downloads/19840011321.pdf","pdf":"/api/citations/19840011321/downloads/19840011321.pdf","fulltext":"/api/citations/19840011321/downloads/19840011321.txt"}}],"downloadsAvailable":true,"index":"submissions-2026-05-21-04-55"},{"_meta":{"score":139.57564},"copyright":{"thirdPartyPermissionsProduced":false,"disclosedToPublic":false,"containsIndication":false,"publisherPermissionOrRightsToDistribute":false,"belongsToUsGov":false,"determinationType":"GOV_PUBLIC_USE_PERMITTED","thirdPartyContentCondition":"NOT_SET","belongsToContractor":false,"disclosedInvention":false,"submissionId":19940018564,"containsThirdPartyMaterial":false,"belongsToPublisher":false,"id":"7e0ee97883fd45e887554f362038e16c","belongsToAuthors":false},"subjectCategories":["Spacecraft Propulsion And Power"],"exportControl":{"isExportControl":"NO","submissionId":19940018564,"ear":"NO","id":"a658d2756ec2447abee383601a1caa04","itar":"NO"},"distributionDate":"2013-08-29T00:00:00.0000000+00:00","title":"SSME fuel preburner injector characterization","stiType":"OTHER","distribution":"PUBLIC","submittedDate":"2013-09-06T19:00:00.0000000+00:00","authorAffiliations":[{"sequence":0,"submissionId":19940018564,"meta":{"author":{"name":"Hutt, John J."},"organization":{"name":"NASA Marshall Space Flight Center","location":"Huntsville, AL, United States"}},"id":"96a5819448ff4ae1993b968c743b0365"}],"stiTypeDetails":"Other","technicalReviewType":"TECHNICAL_REVIEW_TYPE_NONE","modified":"2025-08-31T18:39:21.7150190+00:00","id":19940018564,"legacyMeta":{"__type":"LegacyMetaIndex, StrivesApi.ServiceModel","accessionNumber":"94N23037"},"created":"2013-09-06T19:00:00.0000000+00:00","center":{"code":"CDMS","name":"Legacy CDMS","id":"092d6e0881874968859b972d39a888dc"},"onlyAbstract":false,"sensitiveInformation":2,"abstract":"A project has been initiated at the Marshall Space Flight Center to determine if preburner inter- or intra-element mixture ratio maldistributions are the cause of temperature variations in the Space Shuttle Main Engine (SSME) High Pressure Fuel Turbopump (HPFTP) turbine inlet region. Temperature nonuniformity may contribute to the many problems experienced in this region. The project will involve high pressure cold-flow testing and Computational Fluid Dynamics (CFD) modeling.","isLessonsLearned":false,"disseminated":"DOCUMENT_AND_METADATA","publications":[{"submissionId":19940018564,"id":"f76dadfca6414da3a9682b9068a98f47","publicationName":"Pennsylvania State Univ., NASA Propulsion Engineering Research Center, Volume 2","publicationDate":"1993-11-01T00:00:00.0000000+00:00"}],"status":"CURATED","related":[{"disseminated":"DOCUMENT_AND_METADATA","id":19940018135,"type":"ANALYTIC_PRIMARY","title":"Computational Methods for Failure Analysis and Life Prediction","stiType":"CONFERENCE_PROCEEDINGS","distribution":"PUBLIC","status":"CURATED"},{"disseminated":"DOCUMENT_AND_METADATA","id":19940018135,"type":"ANALYTIC_PRIMARY","title":"Computational Methods for Failure Analysis and Life Prediction","stiType":"CONFERENCE_PROCEEDINGS","distribution":"PUBLIC","accessionNumber":"N94-22609 through N94-22623","status":"CURATED"}],"downloads":[{"draft":false,"mimetype":"application/pdf","name":"19940018564.pdf","type":"STI","links":{"original":"/api/citations/19940018564/downloads/19940018564.pdf","pdf":"/api/citations/19940018564/downloads/19940018564.pdf","fulltext":"/api/citations/19940018564/downloads/19940018564.txt"}}],"downloadsAvailable":true,"index":"submissions-2026-05-21-04-55"},{"_meta":{"score":138.05956},"copyright":{"thirdPartyPermissionsProduced":false,"disclosedToPublic":false,"containsIndication":false,"publisherPermissionOrRightsToDistribute":false,"belongsToUsGov":false,"determinationType":"GOV_PUBLIC_USE_PERMITTED","thirdPartyContentCondition":"NOT_SET","belongsToContractor":false,"disclosedInvention":false,"submissionId":19880004247,"containsThirdPartyMaterial":false,"belongsToPublisher":false,"id":"015e926ead4a4d6b83f01ae015652324","belongsToAuthors":false},"subjectCategories":["Quality Assurance And Reliability"],"exportControl":{"isExportControl":"NO","submissionId":19880004247,"ear":"NO","id":"bca20d72c4d24496b2c77083a2397e9a","itar":"NO"},"distributionDate":"2019-06-24T00:00:00.0000000+00:00","fundingNumbers":[{"number":"NAS8-36700","submissionId":19880004247,"id":"ebbc554bf7c4407cb9ae4b15635d5dfb","type":"CONTRACT_GRANT"}],"title":"Incipient failure detection of space shuttle main engine turbopump bearings using vibration envelope detection","stiType":"CONFERENCE_PAPER","distribution":"PUBLIC","submittedDate":"2013-09-05T17:45:00.0000000+00:00","authorAffiliations":[{"sequence":0,"submissionId":19880004247,"meta":{"author":{"name":"Hopson, Charles B."},"organization":{"name":"Rockwell International Corp.","location":"Huntsville, AL, United States"}},"id":"797d4573052748cd8305c008f5ff7c17"}],"stiTypeDetails":"Conference Paper","technicalReviewType":"TECHNICAL_REVIEW_TYPE_NONE","modified":"2025-08-31T18:39:21.7150190+00:00","id":19880004247,"legacyMeta":{"__type":"LegacyMetaIndex, StrivesApi.ServiceModel","accessionNumber":"88N13629"},"created":"2013-09-05T17:45:00.0000000+00:00","center":{"code":"CDMS","name":"Legacy CDMS","id":"092d6e0881874968859b972d39a888dc"},"onlyAbstract":false,"sensitiveInformation":2,"abstract":"The results of an analysis performed on seven successive Space Shuttle Main Engine (SSME) static test firings, utilizing envelope detection of external accelerometer data are discussed. The results clearly show the great potential for using envelope detection techniques in SSME incipient failure detection.","isLessonsLearned":false,"disseminated":"DOCUMENT_AND_METADATA","publications":[{"submissionId":19880004247,"id":"088ac3c54ed147fd906e53023e767f9b","publicationName":"NASA-Marshall Space Flight Center, The 58th Shock and Vibration Symposium, Volume 1","publicationDate":"1987-10-01T00:00:00.0000000+00:00"}],"status":"CURATED","related":[],"downloads":[{"draft":false,"mimetype":"application/pdf","name":"19880004247.pdf","type":"STI","links":{"original":"/api/citations/19880004247/downloads/19880004247.pdf","pdf":"/api/citations/19880004247/downloads/19880004247.pdf","fulltext":"/api/citations/19880004247/downloads/19880004247.txt"}}],"downloadsAvailable":true,"index":"submissions-2026-05-21-04-55"},{"_meta":{"score":134.19083},"copyright":{"thirdPartyPermissionsProduced":false,"disclosedToPublic":false,"containsIndication":false,"publisherPermissionOrRightsToDistribute":false,"belongsToUsGov":false,"determinationType":"GOV_PUBLIC_USE_PERMITTED","thirdPartyContentCondition":"NOT_SET","belongsToContractor":false,"disclosedInvention":false,"submissionId":19870013365,"containsThirdPartyMaterial":false,"belongsToPublisher":false,"id":"b742e9aed8144ffe9ae21ccc06832f09","belongsToAuthors":false},"subjectCategories":["Spacecraft Propulsion And Power"],"exportControl":{"isExportControl":"NO","submissionId":19870013365,"ear":"NO","id":"5e5ddfd616044d05b937fe2832c4fb16","itar":"NO"},"distributionDate":"2013-08-29T00:00:00.0000000+00:00","title":"SSME blade damper technology","stiType":"CONFERENCE_PAPER","distribution":"PUBLIC","submittedDate":"2013-09-05T09:30:00.0000000+00:00","authorAffiliations":[{"sequence":0,"submissionId":19870013365,"meta":{"author":{"name":"Kielb, Robert E."},"organization":{"name":"NASA Lewis Research Center","location":"Cleveland, OH, United States"}},"id":"f40a01923a8f4b9192441f0a212c0efc"},{"sequence":1,"submissionId":19870013365,"meta":{"author":{"name":"Griffin, Jerry H."},"organization":{"name":"Carnegie-Mellon Univ.","location":"Pittsburgh, Pa., United States"}},"id":"d6571562d46649c3bd095feb3311ca63"}],"stiTypeDetails":"Conference Paper","technicalReviewType":"TECHNICAL_REVIEW_TYPE_NONE","modified":"2025-08-31T18:39:21.7150190+00:00","id":19870013365,"legacyMeta":{"__type":"LegacyMetaIndex, StrivesApi.ServiceModel","accessionNumber":"87N22798"},"created":"2013-09-05T09:30:00.0000000+00:00","center":{"code":"CDMS","name":"Legacy CDMS","id":"092d6e0881874968859b972d39a888dc"},"onlyAbstract":false,"sensitiveInformation":2,"abstract":"Before 1975 turbine blade damper designs were based on experience and very simple mathematical models. Failure of the dampers to perform as expected showed the need to gain a better understanding of the physical mechanism of friction dampers. Over the last 10 years research on friction dampers for aeronautical propulsion systems has resulted in methods to optimize damper designs. The first-stage turbine blades on the Space Shuttle Main Engine (SSME) high-pressure oxygen pump have experienced cracking problems due to excessive vibration. A solution is to incorporate a well-designed friction dampers to attenuate blade vibration. The subject study, a cooperative effort between NASA Lewis and Carnegie-Mellon University, represents an application of recently developed friction damper technology to the SSME high-pressure oxygen turbopump. The major emphasis was the contractor's design known as the two-piece damper. Damping occurs at the frictional interface between the top half of the damper and the underside of the platforms of the adjacent blades. The lower half of the damper is an air seal to retard airflow in the volume between blade necks.","isLessonsLearned":false,"disseminated":"DOCUMENT_AND_METADATA","publications":[{"submissionId":19870013365,"id":"9939fc8df3454aeca56e0c74d0cb1d66","publicationName":"Structural Integrity and Durability of Reusable Space Propulsion Systems","publicationDate":"1987-01-01T00:00:00.0000000+00:00"}],"status":"CURATED","related":[],"downloads":[{"draft":false,"mimetype":"application/pdf","name":"19870013365.pdf","type":"STI","links":{"original":"/api/citations/19870013365/downloads/19870013365.pdf","pdf":"/api/citations/19870013365/downloads/19870013365.pdf","fulltext":"/api/citations/19870013365/downloads/19870013365.txt"}}],"downloadsAvailable":true,"index":"submissions-2026-05-21-04-55"},{"_meta":{"score":124.91354},"copyright":{"thirdPartyPermissionsProduced":false,"disclosedToPublic":false,"containsIndication":false,"publisherPermissionOrRightsToDistribute":false,"belongsToUsGov":false,"determinationType":"GOV_PUBLIC_USE_PERMITTED","thirdPartyContentCondition":"NOT_SET","belongsToContractor":false,"disclosedInvention":false,"submissionId":19800023287,"containsThirdPartyMaterial":false,"belongsToPublisher":false,"id":"aaafddc4464e44398f16928dae016ce4","belongsToAuthors":false},"subjectCategories":["Mechanical Engineering"],"exportControl":{"isExportControl":"NO","submissionId":19800023287,"ear":"NO","id":"6cf3f5d678374528903195f981effc48","itar":"NO"},"distributionDate":"2019-06-21T00:00:00.0000000+00:00","otherReportNumbers":["NASA-CR-161554","Report Number: NASA-CR-161554"],"fundingNumbers":[{"number":"NAS8-33576","submissionId":19800023287,"id":"0320bfa5357e4280988a796629c73db9","type":"CONTRACT_GRANT"}],"title":"SSME turbopump bearing analytical study","stiType":"CONTRACTOR_REPORT","distribution":"PUBLIC","submittedDate":"2013-09-04T16:46:00.0000000+00:00","authorAffiliations":[{"sequence":0,"submissionId":19800023287,"meta":{"author":{"name":"Kannel, J. W."},"organization":{"name":"Battelle Columbus Labs.","location":"OH, United States"}},"id":"e2e5089c8a0449dc9486fbf49b25cc5b"},{"sequence":1,"submissionId":19800023287,"meta":{"author":{"name":"Merriman, T."},"organization":{"name":"Battelle Columbus Labs.","location":"OH, United States"}},"id":"5399710689584eb588dcf2e7af585fe2"}],"stiTypeDetails":"Contractor Report (CR)","technicalReviewType":"TECHNICAL_REVIEW_TYPE_NONE","modified":"2025-08-31T18:39:21.7150190+00:00","id":19800023287,"legacyMeta":{"__type":"LegacyMetaIndex, StrivesApi.ServiceModel","accessionNumber":"80N31794"},"created":"2013-09-04T16:46:00.0000000+00:00","center":{"code":"CDMS","name":"Legacy CDMS","id":"092d6e0881874968859b972d39a888dc"},"onlyAbstract":false,"sensitiveInformation":2,"abstract":"Three shuttle pump bearings operating under severe overspeed and shut-down conditions are evaluated. The specific parameters investigated include outer race stresses, cage stresses, cage-race drag, bearing heating, and crush loading. A quasi-dynamic version of the BASDAP computer code was utilized which involved the calculation of ball-race forces (inner and outer), contact pressures, contact dimensions, and contact angles as a function of (1) axial load, (2) radial load, and (3) centrifugal load on the bearing. Generally, radial loads on the order of 13,300 N (3000 pounds) per bearing or 26,700 N (6000 pounds) per bearing pair, could be expected to cause severe problems to any of the bearings with a 17,800 N (4000 pounds) axial load. Further, when possible temperature excursions are considered, even a load of 8900 N (2000 pounds) may be excessive. However, high momentary radial loads with a 3800 N (850 pounds) axial load would not be anticipated to cause catastrophic failure of the fuel pump bearing.","isLessonsLearned":false,"disseminated":"DOCUMENT_AND_METADATA","publications":[{"submissionId":19800023287,"id":"712c2307e0ef41cfb7aada2b1f5991cb","publicationDate":"1980-08-20T00:00:00.0000000+00:00"}],"status":"CURATED","related":[],"downloads":[{"draft":false,"mimetype":"application/pdf","name":"19800023287.pdf","type":"STI","links":{"original":"/api/citations/19800023287/downloads/19800023287.pdf","pdf":"/api/citations/19800023287/downloads/19800023287.pdf","fulltext":"/api/citations/19800023287/downloads/19800023287.txt"}}],"downloadsAvailable":true,"index":"submissions-2026-05-21-04-55"},{"_meta":{"score":122.20426},"copyright":{"thirdPartyPermissionsProduced":false,"disclosedToPublic":false,"containsIndication":false,"publisherPermissionOrRightsToDistribute":false,"belongsToUsGov":false,"determinationType":"GOV_PUBLIC_USE_PERMITTED","thirdPartyContentCondition":"NOT_SET","belongsToContractor":false,"disclosedInvention":false,"submissionId":19990110696,"containsThirdPartyMaterial":false,"belongsToPublisher":false,"id":"79af23021af242bb963ff23b545c01d7","belongsToAuthors":false},"subjectCategories":["Solid-State Physics"],"exportControl":{"isExportControl":"NO","submissionId":19990110696,"ear":"NO","id":"1a10e6acb05b400099e4e7cf1ecac1a2","itar":"NO"},"distributionDate":"2019-07-12T00:00:00.0000000+00:00","fundingNumbers":[{"number":"NAS8-40836","submissionId":19990110696,"id":"8c703de1db124ad4bc238dd3556e1400","type":"CONTRACT_GRANT"}],"title":"A Study of Single Crystal Fatigue Failure Criteria","stiType":"REPRINT","distribution":"PUBLIC","submittedDate":"2013-08-19T08:09:00.0000000+00:00","authorAffiliations":[{"sequence":0,"submissionId":19990110696,"meta":{"author":{"name":"Sayyah, Tarek"},"organization":{"name":"Sverdrup Technology, Inc.","location":"Huntsville, AL United States"}},"id":"ee02b2a98b054084868df689721a0a78"},{"sequence":1,"submissionId":19990110696,"meta":{"author":{"name":"Swanson, Gregory R."},"organization":{"name":"NASA Marshall Space Flight Center","location":"Huntsville, AL United States"}},"id":"615d21c777dd4c14ad0b2b1abf4a90f8"},{"sequence":2,"submissionId":19990110696,"meta":{"author":{"name":"Schonberg, William P."},"organization":{"name":"Alabama Univ.","location":"Huntsville, AL United States"}},"id":"5b8ed2a6ec84440494ab1bba54ffa158"}],"stiTypeDetails":"Reprint (Version printed in journal)","technicalReviewType":"TECHNICAL_REVIEW_TYPE_NONE","modified":"2025-08-31T18:39:21.7150190+00:00","id":19990110696,"legacyMeta":{"__type":"LegacyMetaIndex, StrivesApi.ServiceModel","accessionNumber":""},"created":"2013-08-19T08:09:00.0000000+00:00","center":{"code":"MSFC","name":"Marshall Space Flight Center","id":"a589fc1e68af409f9d2214bb08863d11"},"onlyAbstract":false,"sensitiveInformation":2,"abstract":"This paper presents the results of a study whose objective was to study the applicability of different failure equations in modeling low cycle fatigue (LCF) test data for single crystal test specimens. A total of four failure criteria were considered in this study. One of the failure equations was developed by Pratt & Whitney and is based on normal and shear strains on the primary crystallographic slip planes of the single crystal material. Other failure equations considered are based on isotropic criteria. Because these failure equations were originally developed for isotropic materials such as structural steel, they were modified to be applicable to the single crystal slip systems of the LCF specimen material. By observing how closely the various equations were able to reduce the scatter in the LCF test data, the applicability of those equations in modeling the LCF test data was assessed. It is desired to subsequently use the failure equation with the highest correlation in the development of a new single crystal failure criterion for the Alternative Turbopump Development (ATD) for the space shuttle main engine (SSME) High Pressure Fuel Turbopump (HPFTP).","isLessonsLearned":false,"disseminated":"METADATA_ONLY","meetings":[{"country":"United States","submissionId":19990110696,"endDate":"2000-03-02T00:00:00.0000000+00:00","sponsors":[{"organizationId":"2ef1e139aeb54023adde3e61d91a3ed6","meta":{"organization":{"name":"American Society of Chemical Engineers","location":"United States"}},"meetingId":"e6edd7359fa24a69a83e8e631653f0c4","id":"38da64286eb1447f8bc81ab1e9c098fa"}],"name":"Space and Robotics 2000","location":"Albuquerque, NM","id":"e6edd7359fa24a69a83e8e631653f0c4","startDate":"2000-02-28T00:00:00.0000000+00:00"}],"publications":[{"submissionId":19990110696,"id":"9fb77a4ef1434eeca90aa5c9c5b4818d","publicationDate":"2000-01-01T00:00:00.0000000+00:00"}],"status":"CURATED","related":[],"downloads":[],"downloadsAvailable":false,"index":"submissions-2026-05-21-04-55"}],"aggregations":{"created":{"buckets":[{"key_as_string":"2013","key":1356998400000,"doc_count":38}]},"author":{"doc_count_error_upper_bound":0,"sum_other_doc_count":47,"buckets":[{"key":"Swanson, Gregory R.","doc_count":3},{"key":"Arakere, Nagaraj K.","doc_count":2},{"key":"Dreshfield, R. L.","doc_count":2},{"key":"Kannel, J. W.","doc_count":2},{"key":"Parr, R. A.","doc_count":2},{"key":"Sayyah, Tarek","doc_count":2},{"key":"American Institute of Aeronautics and Astronautics","doc_count":1},{"key":"Anderson, P. G.","doc_count":1},{"key":"Chamis, C. C.","doc_count":1},{"key":"Chamis, Christos C.","doc_count":1},{"key":"Childs, D. W.","doc_count":1},{"key":"Cody, J. C.","doc_count":1},{"key":"Coffin, T.","doc_count":1},{"key":"Cook, M. B.","doc_count":1},{"key":"Darrell Gaddy","doc_count":1},{"key":"Dejong, F. J.","doc_count":1},{"key":"Dufrane, K. F.","doc_count":1},{"key":"Englund, D. R.","doc_count":1},{"key":"Farmer, R. C.","doc_count":1},{"key":"Farr, R. A.","doc_count":1}]},"reportNumber":{"doc_count_error_upper_bound":0,"sum_other_doc_count":80,"buckets":[{"key":"AIAA PAPER 87-1976","doc_count":2},{"key":"Report Number: AIAA PAPER 87-1976","doc_count":2},{"key":"AIAA PAPER 89-2348","doc_count":1},{"key":"AIAA Paper 2002","doc_count":1},{"key":"AISR-TR-4002-93-09","doc_count":1},{"key":"ASME-Trib-61","doc_count":1},{"key":"BCD-SSME-TR-87-1","doc_count":1},{"key":"CI-IR-0079","doc_count":1},{"key":"E-13662-2/PT2","doc_count":1},{"key":"E-3556","doc_count":1},{"key":"E-4855","doc_count":1},{"key":"E-5897","doc_count":1},{"key":"E-6068","doc_count":1},{"key":"LMSC-HEC-TR-F268627","doc_count":1},{"key":"M-1096","doc_count":1},{"key":"M-780","doc_count":1},{"key":"M10-0303","doc_count":1},{"key":"NAS 1.15:100393","doc_count":1},{"key":"NAS 1.15:102091","doc_count":1},{"key":"NAS 1.15:103557","doc_count":1}]},"center":{"doc_count_error_upper_bound":0,"sum_other_doc_count":0,"buckets":[{"key":"CDMS","doc_count":28},{"key":"MSFC","doc_count":9},{"key":"GRC","doc_count":1}]},"index":{"doc_count_error_upper_bound":0,"sum_other_doc_count":0,"buckets":[{"key":"submissions-2026-05-21-04-55","doc_count":38}]},"fundingNumber":{"doc_count_error_upper_bound":0,"sum_other_doc_count":0,"buckets":[{"key":"NAG3-1163","doc_count":2},{"key":"NAS8-40836","doc_count":2},{"key":"RTOP 260-40-03","doc_count":2},{"key":"RTOP 553-13-00","doc_count":2},{"key":"NAS3-23349","doc_count":1},{"key":"NAS8-33221","doc_count":1},{"key":"NAS8-33576","doc_count":1},{"key":"NAS8-34505","doc_count":1},{"key":"NAS8-35506","doc_count":1},{"key":"NAS8-36700","doc_count":1},{"key":"NAS8-36801","doc_count":1},{"key":"NAS8-37302","doc_count":1},{"key":"NAS8-39393","doc_count":1},{"key":"NAS8-45000","doc_count":1},{"key":"NASW-3737","doc_count":1},{"key":"RTOP 506-43-11","doc_count":1},{"key":"RTOP 553-13","doc_count":1},{"key":"RTOP 590-21-11-300","doc_count":1}]},"published":{"buckets":[{"key_as_string":"1985","key":473385600000,"doc_count":5},{"key_as_string":"1987","key":536457600000,"doc_count":5},{"key_as_string":"1989","key":599616000000,"doc_count":3},{"key_as_string":"1990","key":631152000000,"doc_count":3},{"key_as_string":"1993","key":725846400000,"doc_count":3},{"key_as_string":"1999","key":915148800000,"doc_count":3},{"key_as_string":"2000","key":946684800000,"doc_count":3},{"key_as_string":"1984","key":441763200000,"doc_count":2},{"key_as_string":"1991","key":662688000000,"doc_count":2},{"key_as_string":"1994","key":757382400000,"doc_count":2},{"key_as_string":"1979","key":283996800000,"doc_count":1},{"key_as_string":"1980","key":315532800000,"doc_count":1},{"key_as_string":"1995","key":788918400000,"doc_count":1},{"key_as_string":"2002","key":1009843200000,"doc_count":1},{"key_as_string":"2003","key":1041379200000,"doc_count":1},{"key_as_string":"2004","key":1072915200000,"doc_count":1},{"key_as_string":"2010","key":1262304000000,"doc_count":1}]},"distribution":{"doc_count_error_upper_bound":0,"sum_other_doc_count":0,"buckets":[{"key":"PUBLIC","doc_count":38}]},"stiType":{"doc_count_error_upper_bound":0,"sum_other_doc_count":0,"buckets":[{"key":"CONFERENCE_PAPER","doc_count":12},{"key":"CONTRACTOR_REPORT","doc_count":8},{"key":"CONFERENCE_PROCEEDINGS","doc_count":4},{"key":"TECHNICAL_MEMORANDUM","doc_count":4},{"key":"PREPRINT","doc_count":3},{"key":"ABSTRACT","doc_count":2},{"key":"OTHER","doc_count":2},{"key":"REPRINT","doc_count":2},{"key":"TECHNICAL_PUBLICATION","doc_count":1}]},"subjectCategory":{"doc_count_error_upper_bound":0,"sum_other_doc_count":0,"buckets":[{"key":"Spacecraft Propulsion And Power","doc_count":13},{"key":"Mechanical Engineering","doc_count":8},{"key":"Structural Mechanics","doc_count":4},{"key":"Metallic Materials","doc_count":2},{"key":"Aeronautics (General)","doc_count":1},{"key":"Aircraft Propulsion And Power","doc_count":1},{"key":"Chemistry And Materials (General)","doc_count":1},{"key":"Earth Resources And Remote Sensing","doc_count":1},{"key":"Engineering (General)","doc_count":1},{"key":"Fluid Mechanics And Heat Transfer","doc_count":1},{"key":"Metals And Metallic Materials","doc_count":1},{"key":"Quality Assurance And Reliability","doc_count":1},{"key":"Solid-State Physics","doc_count":1},{"key":"Space Transportation","doc_count":1},{"key":"Spacecraft Instrumentation","doc_count":1}]},"disseminated":{"doc_count_error_upper_bound":0,"sum_other_doc_count":0,"buckets":[{"key":"DOCUMENT_AND_METADATA","doc_count":27},{"key":"METADATA_ONLY","doc_count":11}]},"stiTypeDetails":{"doc_count_error_upper_bound":0,"sum_other_doc_count":0,"buckets":[{"key":"Conference Paper","doc_count":12},{"key":"Contractor Report (CR)","doc_count":8},{"key":"Conference Proceedings","doc_count":4},{"key":"Technical Memorandum (TM)","doc_count":4},{"key":"Preprint (Draft being sent to journal)","doc_count":3},{"key":"Abstract","doc_count":2},{"key":"Other","doc_count":2},{"key":"Reprint (Version printed in journal)","doc_count":2},{"key":"Technical Publication (TP)","doc_count":1}]},"organization":{"doc_count_error_upper_bound":0,"sum_other_doc_count":5,"buckets":[{"key":"NASA Marshall Space Flight Center","doc_count":13},{"key":"NASA Lewis Research Center","doc_count":7},{"key":"Battelle Columbus Labs.","doc_count":3},{"key":"Rockwell International Corp.","doc_count":3},{"key":"Alabama Univ.","doc_count":2},{"key":"Florida Univ.","doc_count":2},{"key":"Michigan Univ.","doc_count":2},{"key":"A. M. Consulting","doc_count":1},{"key":"AI Signal Research, Inc.","doc_count":1},{"key":"Boeing Co.","doc_count":1},{"key":"Carnegie-Mellon Univ.","doc_count":1},{"key":"Continuum, Inc.","doc_count":1},{"key":"Lockheed Martin Space Systems Co.","doc_count":1},{"key":"Lockheed Missiles and Space Co.","doc_count":1},{"key":"Marshall Space Flight Center","doc_count":1},{"key":"NASA  Marshall Space Flight Center","doc_count":1},{"key":"NASA Glenn Research Center","doc_count":1},{"key":"Pratt and Whitney Aircraft","doc_count":1},{"key":"Pratt and Whitney Rocketdyne","doc_count":1},{"key":"Scientific Research Associates, Inc.","doc_count":1}]},"modified":{"buckets":[{"key_as_string":"2025","key":1735689600000,"doc_count":38}]},"keyword":{"doc_count_error_upper_bound":0,"sum_other_doc_count":0,"buckets":[]}}}